AD 2017-18-09

We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, CN- 235-300, and C-295 airplanes. This AD was prompted by reports of excessive play between bushings and their respective fitting housings at certain elevator fittings. This AD requires a one-time detailed inspection and repetitive eddy current inspections of the elevator hinge fitting and bracket assembly, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.

Final rule.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0 1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD):

2017-18-09 Airbus Defense and Space S.A. (Formerly Known as Construcciones Aeronauticas, S.A.): Amendment 39-19018; Docket No. FAA-2016-9521; Product Identifier 2016-NM-061-AD.

(a) Effective Date

This AD is effective October 10, 2017.

(b) Affected ADs

None.

(c) Applicability

This AD applies to Airbus Defense and Space S.A. (formerly known as Construcciones Aeronauticas, S.A.) Model CN-235, CN-235-100, CN- 235-200, CN-235-300, and C-295 airplanes, certificated in any category, all manufacturer serial numbers.

(d) SubjectAir Transport Association (ATA) of America Code 55, Stabilizers.

[[Page 41880]]

(e) Reason

This AD was prompted by reports of excessive play between bushings and their respective fitting housings at certain elevator fittings. We are issuing this AD to prevent excessive play between bushings and their respective fitting housings, which could lead to failure or detachment of any of the affected structural parts, with a possible result of reduced control of the airplane.

(f) Compliance

Comply with this AD within the compliance times specified, unless already done.

(g) One-Time Detailed Visual Inspection

Before exceeding 600 flight hours since first flight of the airplane, or within 300 flight hours after the effective date of this AD, whichever occurs later, but not before exceeding 300 flight hours since first flight of the airplane: Do a detailed visual inspection of the elevator hinge fitting and bracket assembly to detect excessive play between bushings and their respective fitting housings, and to detect cracks, in accordance with the instructions of Airbus Defense and Space S.A. Alert Operators Transmission (AOT) AOT-CN235-55-0001, Revision 2, dated March 10, 2015; or AOT AOT- C295-55-0001, Revision 2, dated April 9, 2015; as applicable.

(h) Corrective Action for Discrepancies Found During Detailed Visual Inspection

If, during the inspection required by paragraph (g) of this AD, any discrepancy is detected, as defined in the instructions of Airbus Defense and Space S.A. AOT AOT-CN235-55-0001, Revision 2, dated March 10, 2015; or AOT AOT-C295-55-0001 Revision 2, dated April 9, 2015; as applicable: Before further flight, accomplish applicable corrective actions, in accordance with the instructions of Airbus Defense and Space S.A. AOT AOT-CN235-55-0001, Revision 2, dated March 10, 2015; or AOT AOT-C295-55-0001, Revision 2, dated April 9, 2015; as applicable. Where Airbus Defense and Space S.A. AOT AOT-CN235-55-0001, Revision 2, dated March 10, 2015; or AOT AOT- C295-55-0001 Revision 2, dated April 9, 2015; specifies to contact Airbus Defense and Space S.A. for corrective actions, before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (n)(2) of this AD.

(i) Repetitive Eddy Current Inspections--Model CN-235, CN-235-100, CN- 235-200, and CN-235-300 Airplanes

For Model CN-235, CN-235-100, CN-235-200, and CN-235-300 airplanes: Do the actions required by paragraphs (i)(1) and (i)(2) of this AD.
(1) Within the applicable compliance time specified in table 1 to paragraph (i)(1) of this AD: Do an eddy current inspection to detect cracks in the elevator hinge fitting and bracket assembly, in accordance with the instructions of Airbus Defense and Space S.A. AOT AOT-CN235-55-0003, dated December 22, 2015.

Table 1 to Paragraph (i)(1) of This AD--Initial Compliance Times for Model CN-235, CN-235-100, CN-235-200, and
CN-235-300Airplanes ----------------------------------------------------------------------------------------------------------------

---------------------------------------------------------------------------------------------------------------- Manufacturer's Serial No. Elevator hinge fitting Compliance time for initial eddy current
inspection (MSN) (part No.) (whichever occurs later) ---------------------------------------------------------------------------------------------------------------- MSN001 through MSN154 inclusive.... 35-31193-0201 Before exceeding 8,800 Within 300 flight
35-31193-0202 flight cycles since first cycles after the
flight of the airplane; or effective date of
before exceeding the this AD.
applicable flight hours
since first flight of the
airplane as calculated in
table 2 to paragraph
(i)(1) of this AD;
whichever occurs first. MSN155 through MSN241 inclusive.... 35-31193-0501 Before exceeding 3,600 Within 300 flight
35-31193-0502 flight cycles since first cycles after the
flight of the airplane; or effective date of
before exceeding the this AD.
applicable flight hours
since first flight of the
airplane as calculated in
table 2 to paragraph
(i)(1) of this AD;
whichever occurs first. MSN242 through MSN999 inclusive.... 35-31193-0503 Before exceeding 1,000 Within 50 flight
35-31193-0504 flight cycles since first cycles after the
flight of the airplane; or effective date of
before exceeding the this AD.
applicable flight hours
since first flight of the
airplane as calculated in
table 2 to paragraph
(i)(1) of this AD;
whichever occurs first. ----------------------------------------------------------------------------------------------------------------

Table 2 to Paragraph (i)(1) of This AD--Flight Cycles to Flight Hours
Conversion Since First Flight of the Airplane ------------------------------------------------------------------------
Civilian or Flight cycles to
CN-235 Model/version military type flight hours
certificate conversion ------------------------------------------------------------------------ CN-235 (Commercial Civilian......... Flight hours since
Identification S10). first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 0.861. CN-235-100.................... Civilian......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 0.861. CN-235-200.................... Civilian......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 0.806. CN-235-300.................... Civilian......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 0.861. CN-235 (Commercial Military......... Flight hours since
Identification S10M). first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 0.861. CN-235-100M................... Military......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 2.222. CN-235-200M................... Military......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 2.222. CN-235-300M................... Military......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 2.167. CN-235-100M/IR01.............. Military......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 1.389. CN-235-100M/EA02V............. Military......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 1.389.

[[Page 41881]]

CN-235-200M/CL02.............. Military......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 1.389. CN-235/EA01F (Commercial Military......... Flight hours since
Identification S10M). first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 0.861. CN-235-300/SM01............... Civilian......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 3.125. CN-235 -300M/CG01, -300M/GC01, Military......... Flight hours since
-300/MM01, -300/CL04. first flight of the
airplane = the
applicable flight
cycles from table 1
to paragraph (i)(1)
of this AD x 3.125. ------------------------------------------------------------------------

(2) Repeat the eddy current inspection specified in paragraph (i)(1) of this AD thereafter within the applicable interval specified in table 3 to paragraph (i)(2) of this AD.

Table 3 to Paragraph (i)(2) of This AD--Repetitive Inspection Intervals ------------------------------------------------------------------------
Elevator Compliance time for
Manufacturer's serial No. attachment repetitive eddy
fitting (P/N) current inspections ------------------------------------------------------------------------ MSN001 through MSN154 35-31193-0201 Before exceeding
inclusive. 35-31193-0202 1,300 flight cycles
since the most
recent inspection;
or before exceeding
the applicable
flight hours since
the most recent
inspection as
calculated in table
4 to paragraph
(i)(2) of this AD;
whichever occurs
first. MSN155 through MSN241 35-31193-0501 Before exceeding
inclusive. 35-31193-0502 1,000 flight cycles
since the most
recent inspection;
or before exceeding
the applicable
flight hours since
the most recent
inspection as
calculated in table
4 to paragraph
(i)(2) of this AD;
whichever occurs
first. MSN242 through MSN999 35-31193-0503 Before exceeding
inclusive. 35-31193-0504 1,000 flight cycles
since the most
recent inspection;
or before exceedingthe applicable
flight hours since
the most recent
inspection as
calculated in table
4 to paragraph
(i)(2) of this AD;
whichever occurs
first. ------------------------------------------------------------------------

Table 4 to Paragraph (i)(2) of This AD--Flight Cycles to Flight Hours
Conversion for Repetitive Inspections ------------------------------------------------------------------------
Civilian or Flight cycles to
CN-235 Model/version military type flight hours
certificate conversion ------------------------------------------------------------------------ CN-235 (Commercial Civilian......... Flight hours since
Identification S10). most recent
inspection = the
applicable flight
cycles from table 3
to paragraph (i)(2)
of this AD x 0.861. CN-235-100.................... Civilian......... Flight hours since
most recent
inspection =the
applicable flight
cycles from table 3
to paragraph (i)(2)
of this AD x 0.861. CN-235-200.................... Civilian......... Flight hours since
most recent
inspection = the
applicable flight
cycles from table 3
to paragraph (i)(2)
of this AD x 0.806. CN-235-300.................... Civilian......... Flight hours since
first flight of the
airplane = the
applicable flight
cycles from table 3
to paragraph (i)(2)
of this AD x 0.861. CN-235 (Commercial Military......... Flight hours since
Identification S10M). most recent
inspection = the
applicable flight
cycles from table 3
to paragraph (i)(2)
of this AD x 0.861. CN-235-100M................... Military......... Flight hours since
most recent
inspection = the
applicable flight
cycles from table 3
to paragraph (i)(2)
of this AD x 2.222. CN-235-200M................... Military......... Flight hours sincemost recent
inspection = the
applicable flight
cycles from table 3
to paragraph (i)(2)
of this AD x 2.222. CN-235-300M................... Military......... Flight hours since
most recent
inspection = the
applicable flight
cycles from table 3
to paragraph (i)(2)
of this AD x 2.167. CN-235-100M/IR01.............. Military......... Flight hours since
most recent
inspection = the
applicable flight
cycles from table 3
to paragraph (i)(2)
of this AD x 1.389. CN-235-100M/EA02V............. Military......... Flight hours since
most recent
inspection = the
applicable flight
cycles from table 3
to paragraph (i)(2)
of this AD x 1.389. CN-235-200M/CL02.............. Military......... Flight hours since
most recent
inspection = the
applicable flight
cycles from table 3
to paragraph (i)(2)
of this AD x 1.389. CN-235/EA01F (Commercial Military......... Flight hours since
Identification S10M).most recent
inspection = the
applicable flight
cycles from table 3
to paragraph (i)(2)
of this AD x 0.861. CN-235-300/SM01............... Civilian......... Flight hours since
most recent
inspection = the
applicable flight
cycles from table 3
to paragraph (i)(2)
of this AD x 3.125. CN-235 -300M/CG01, -300M/GC01, Military......... Flight hours since
-300/MM01, -300/CL04. most recent
inspection = the
applicable flight
cycles from table 3
to paragraph (i)(2)
of this AD x 3.125. ------------------------------------------------------------------------

[[Page 41882]]

(j) Repetitive Eddy Current Inspections--Model C-295 Airplanes

For Model C-295 airplanes: Do the actions required by paragraphs (j)(1) and (j)(2) of this AD.
(1) At the later of the times specified in table 5 to paragraph (j)(1) of this AD: Do an eddy current inspection of the elevator hinge fitting and attachment fitting to detect cracks, in accordance with the instructions of Airbus Defense and Space S.A. AOT AOT-C295- 55-0003, dated December 22, 2015.

Table 5 to Paragraph (j)(1) of This AD--Initial Compliance Times for Model C-295 Airplanes ----------------------------------------------------------------------------------------------------------------

---------------------------------------------------------------------------------------------------------------- C-295 Model/Version Manufacturer's Elevator Hinge Compliance time for initial eddy current
Serial Number. Fitting inspection
(MSN)............ (Part Number) (whichever occurs later) ---------------------------------------------------------------------------------------------------------------- C-295M/ EA03(01-10), RJ01 (01- MSN001 through 95-31193-0501 Since first flight of Within 300 flight
02), PO01(01-08), AG01(01-06), MSN030 inclusive. 95-31193-0502 the airplane: Before cycles after the
BR01(01-03). exceeding 3,600 effective date
flight cycles; or of this AD.
before exceeding
5,040 flight hours;
whichever occurs
first. C-295M (from MSN 031).......... MSN031 through 95-31193-0503 Since first flight of Within 50 flight
MSN999 inclusive. 95-31193-0504 the airplane: Before cycles after the
exceeding 1,000 effective date
flight cycles; or of this AD.
before exceeding
1,400 flight hours;
whichever occurs
first. C-295M/FI01, FI02.............. MSN031 through 95-31193-0503 Since first flight of Within 50 flight
MSN999 inclusive. 95-31193-0504 the airplane: Before cycles after the
exceeding 1,000 effective date
flight cycles; or of this AD.
before exceeding
1,000 flight hours;
whichever occursfirst. C-295M/PG01.................... MSN031 through 95-31193-0503 Since first flight of Within 50 flight
MSN999 inclusive. 95-31193-0504 the airplane: Before cycles after the
exceeding 1,000 effective date
flight cycles; or of this AD.
before exceeding
1,400 flight hours;
whichever occurs
first. C-295M/PG02, PG03.............. MSN031 through 95-31193-0503 Since first flight of Within 50 flight
MSN999 inclusive. 95-31193-0504 the airplane: Before cycles after the
exceeding 1,000 effective date
flight cycles; or of this AD.
before exceeding
1,900 flight hours;
whichever occurs
first. C-295M/CH01.................... MSN031 through 95-31193-0503 Since first flight of Within 50 flight
MSN999 inclusive. 95-31193-0504 the airplane: Before cycles after the
exceeding 1,000 effective date
flight cycles; or of this AD.
before exceeding1,200 flight hours;
whichever occurs
first. C-295M/CH02, OM03.............. MSN031 through 95-31193-0503 Since first flight of Within 50 flight
MSN999 inclusive. 95-31193-0504 the airplane: Before cycles after the
exceeding 1,000 effective date
flight cycles; or of this AD.
before exceeding
1,500 flight hours;
whichever occurs
first. C-295MW........................ MSN031 through 95-31193-0503 Since first flight of Within 50 flight
MSN999 inclusive. 95-31193-0504 the airplane: Before cycles after the
exceeding 1,000 effective date
flight cycles; or of this AD.
before exceeding
1,400 flight hours;
whichever occurs
first. ----------------------------------------------------------------------------------------------------------------

(2) Repeat the eddy current inspection specified in paragraph (j)(1) of this AD thereafter within the applicable interval specified in table 6 to paragraph (j)(2) of this AD.

Table 6 to Paragraph (j)(2) of This AD--Repetitive Inspection Intervals for Model C-295 Airplanes ----------------------------------------------------------------------------------------------------------------
Elevator hinge Compliance time for
C-295 Model/version Manufacturer's serial fitting (part repetitive eddy current
No. (MSN) number) inspections ---------------------------------------------------------------------------------------------------------------- C-295M/ EA03(01-10), RJ01 (01-02), MSN001 through MSN030 95-31193-0501 Before exceeding 1,000
PO01(01-08), AG01(01-06), BR01(01- inclusive. 95-31193-0502 flight cycles since the
03). most recent inspection; or
before exceeding 1,400
flight hours since the most
recent inspection;
whichever occurs first. C-295M (from MSN 031)................ MSN031 through MSN999 95-31193-0503 Before exceeding 1,000
inclusive. 95-31193-0504 flight cycles since the
most recent inspection; or
before exceeding 1,400
flight hours since the most
recent inspection;
whichever occurs first. C-295M/FI01, FI02.................... MSN031 through MSN999 95-31193-0503 Before exceeding 1,000
inclusive. 95-31193-0504 flight cycles since the
most recent inspection; or
before exceeding 1,000
flight hours since the most
recent inspection;
whichever occurs first. C-295M/PG01.......................... MSN031 through MSN999 95-31193-0503 Before exceeding 1,000
inclusive. 95-31193-0504 flight cycles since the
most recent inspection; or
before exceeding 1,400
flight hours since the most
recent inspection;
whichever occurs first. C-295M/PG02, PG03.................... MSN031 through MSN999 95-31193-0503 Before exceeding 1,000
inclusive. 95-31193-0504 flight cycles since the
most recent inspection; or
before exceeding 1,900
flight hours since the most
recent inspection;
whichever occurs first.

[[Page 41883]]

C-295M/CH01.......................... MSN031 through MSN999 95-31193-0503 Before exceeding 1,000
inclusive. 95-31193-0504 flight cycles since the
most recent inspection; or
before exceeding 1,200
flight hours since the most
recent inspection;
whichever occurs first. C-295M/CH02, OM03.................... MSN031 through MSN999 95-31193-0503 Before exceeding 1,000
inclusive. 95-31193-0504 flight cycles since the
most recent inspection; or
before exceeding 1,500
flight hours since the most
recent inspection;
whichever occurs first. C-295MW.............................. MSN031 through MSN99995-31193-0503 Before exceeding 1,000
inclusive. 95-31193-0504 flight cycles since the
most recent inspection; or
before exceeding 1,400
flight hours since the most
recent inspection;
whichever occurs first. ----------------------------------------------------------------------------------------------------------------

(k) Corrective Action for Discrepancies Found During Eddy Current Inspection

If, during any inspection required by paragraph (i)(1), (i)(2), (j)(1), or (j)(2) of this AD, any crack is detected, as defined in Airbus Defense and Space S.A. AOT AOT-CN235-55-0003, dated December 22, 2015; or AOT AOT-C295-55-0003, dated December 22, 2015; as applicable: Before further flight, accomplish applicable corrective actions in accordance with the instructions of Airbus Defense and Space S.A. AOT AOT-CN235-55-0003, dated December 22, 2015; or AOT AOT-C295-55-0003, dated December 22, 2015; as applicable. Where Airbus Defense andSpace S.A. AOT AOT-CN235-55-0003, dated December 22, 2015; or AOT AOT-C295-55-0003, dated December 22, 2015; specifies to contact Airbus Defense and Space S.A. for corrective actions, before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (n)(2) of this AD.

(l) Provision Regarding Terminating Action

Accomplishing corrective actions, as required by paragraph (k) of this AD, does not constitute terminating action for the repetitive inspections required by paragraphs (i)(2) and (j)(2) of this AD, unless explicitly stated in the approved method of compliance for the corrective action.

(m) Credit for Previous Actions

This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Defense and Space S.A. AOT AOT-CN235-55-0001, Revision 1, dated March 6, 2015; or AOT AOT-C295- 55-0001, Revision 1, dated May 29, 2014.

(n) Other FAA AD Provisions

The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office.
(2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus Defense and Space S.A.'s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.

(o) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0075, dated April 19, 2016, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9521.
(2) For more information about this AD, contact Shahram Daneshmandi, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1112; fax: 425-227-1149.
(3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(3) and (p)(4) of this AD.

(p) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Defense and Space S.A. Alert Operators Transmission (AOT) AOT-CN235-55-0001, Revision 2, dated March 10, 2015.
(ii) Airbus Defense and Space S.A. AOT AOT-CN235-55-0003, dated December 22, 2015.
(iii) Airbus Defense and Space S.A. AOT AOT-C295-55-0001, Revision 2, dated April 9, 2015.
(iv) Airbus Defense and Space S.A. AOT AOT-C295-55-0003, dated December 22, 2015.
(3) For service information identified in this AD, contact Airbus Defense and Space, Services/Engineering Support, Avenida de Arag[oacute]n 404, 28022 Madrid, Spain; fax +34 91 585 31 27; email MTA.TechnicalService@airbus.com.
(4) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221.
(5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, CN-235-300, and C-295 airplanes. The NPRM published in the Federal Register on January 5, 2017 (82 FR 1269) (``the NPRM''). The NPRM was prompted by reports of excessive play between bushings and their respective fitting housings at certain elevator fittings. The NPRM proposed to require a one-time detailed inspection and repetitive eddy current inspections of the elevator hinge fitting and bracket assembly, and corrective actions if necessary. We are issuing this AD to prevent excessive play between bushings and their respective fitting housings, which could lead to failure or detachment of any of the affected structural parts, with a possible result of reduced control of the airplane.
The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016-0075, dated April 19, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, CN-235-300, and C-295 airplanes. The MCAI states:

Excessive play between bushings and their respective fitting housing was reported at Stabilizer Station (STA) 4850, affecting the outboard and inboard elevator hinge fittings and attachment fittings; and the horizontal stabilizer elevator linkage. Additionally, excessive misalignment was detected between the elevator hinge fittings and the elevator brackets during further analysis of the reported cases. Furthermore, an occurrence of an elevator hinge fitting crack was reported.
This condition, if not detected and corrected, could lead to failure or detachment of any of the affected structural parts, possibly resulting in reduced control of the aeroplane.
To address this potentially unsafe condition, Airbus Defence & Space (D&S) issued Alert Operator Transmissions (AOT) AOT-CN235-55- 0001 Revision 2 and AOT-C295-55-0001 Revision 2 to provide inspection instructions to detect misalignment between the elevator hinge fittings and the elevator brackets. Additionally, Airbus D&S issued AOT-CN235-55-0003 and AOT-C295-55-0003 to provide inspection instructions to detect cracking of elevator hinge fitting and attachment fitting.
For the reasons described above, this [EASA] AD requires a one- time [detailed] inspection of the elevator hinge fittings and the elevator brackets, repetitive [eddy current] inspections of elevator hinge fittings and attachment fittings, and depending on findings, accomplishment of applicable corrective action(s) [e.g. repair(s)].

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 9521.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public.

Conclusion

We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed, except for minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

Airbus Defense and Space S.A. has issued the following Alert Operators Transmissions (AOT).
Airbus Defense and Space S.A. AOT AOT-CN235-55-0001, Revision 2, dated March 10, 2015. The service information describes procedures for a detailed visual inspection of the elevator hinge fitting and bracket assembly to detect excessive play between bushings and their respective fitting housings, and to detect cracks; and corrective actions if necessary.
Airbus Defense and Space S.A. AOT AOT-CN235-55-0003, dated December 22, 2015. The service

[[Page 41879]]

information describes procedures for repetitive eddy current inspections to detect cracks in the elevator hinge fitting and bracket assembly, and corrective actions if necessary.
Airbus Defense and Space S.A. AOT AOT-C295-55-0001, Revision 2, dated April 9, 2015. The service information describes procedures for a detailed visual inspection of the elevator hinge fitting and bracket assembly to detect excessive play between bushings and their respective fitting housings, and to detect cracks; and corrective actions if necessary.
Airbus Defense and Space S.A. AOT AOT-C295-55-0003, dated December 22, 2015. The service information describes procedures for repetitive eddy current inspections to detect cracks in the elevator hinge fitting and bracket assembly, and corrective actions if necessary.
These documents are distinct since they apply to different airplane models in different configurations. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section.

Costs of Compliance

We estimate that this AD affects 14 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:

Estimated Costs ----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection........................ 2 work-hours x $85 $0 $170 per inspection $2,380 per
per hour = $170 per cycle.inspection cycle.
inspection cycle. ----------------------------------------------------------------------------------------------------------------

We estimate the following costs to do any necessary repairs that will be required based on the results of the inspection. We have no way of determining the number of airplanes that might need this repair:

On-Condition Costs ----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Repair....................................... 45 work-hours x $85 per hour = $10,000 $13,825
$3,825. ----------------------------------------------------------------------------------------------------------------

Authority for This RulemakingTitle 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordancewith that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division.

Regulatory Findings

We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order 12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.