AD 2017-26-08

We are adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R[eacute]gional Model ATR42-500 and ATR72- 212A airplanes. This AD requires revising the airplane flight manual (AFM) to provide procedures to the flight crew for operational restrictions affecting in-flight use of the autopilot (AP) or yaw damper (YD) during dual-engine operation. This AD also provides an optional software modification, which would terminate the AFM requirement. This AD was prompted by flight test evaluations that revealed that after engine failure during AP or YD re-engagement, the YD unit commanded the rudder to return to neutral position, leading to inadequate balancing of the asymmetric power. We are issuing this AD to address the unsafe condition on these products.

Final rule; request for comments.

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):

2017-26-08 ATR-GIE Avions de Transport R[eacute]gional: Amendment 39-19139; Docket No. FAA-2017-1177; Product Identifier 2015-NM-195- AD.

(a) Effective Date

This AD becomes effective January 18, 2018.

(b) Affected ADs

None.

(c) Applicability

This AD applies to ATR-GIE Avions de Transport R[eacute]gional Model ATR42-500 airplanes, and Model ATR72-212A airplanes; certificated in any category; all manufacturer serial numbers on which ATR-GIE Avions de Transport R[eacute]gional Modification 5948 (New Avionics Suite installation)has been embodied in production, except those airplanes identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) Airplanes on which ATR-GIE Avions de Transport R[eacute]gional Mod 6977 (New Avionics Suite Standard 2) has been embodied in production.
(2) Airplanes on which ATR Service Bulletin ATR42-31-0091, or ATR Service Bulletin ATR72-31-1092, has been incorporated.

(d) Subject

Air Transport Association (ATA) of America Code 31, Instruments.

(e) Reason

This AD was prompted by flight evaluations that revealed that after engine failure during autopilot (AP) or yaw damper (YD) re- engagement, the YD unit commanded the rudder to return to neutral position, leading to inadequate balancing of the asymmetric power. We are issuing this AD to provide procedures to the flightcrew for operational restrictions affecting in-flight use of the autopilot (AP) or yaw damper (YD) during dual-engine operation.

(f) Compliance

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

(g) Revise the Airplane Flight Manual

Within 30 days after the effective date of this AD, revise the Limitations Section of the

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applicable ATR-42 and ATR-72 airplane flight manuals (AFMs) to include figure 1 to paragraph (g) of this AD. Amending the AFM of an airplane by inserting a copy of this AD into the applicable AFM of that airplane is acceptable to comply with the requirements of this paragraph for that airplane. [GRAPHIC] [TIFF OMITTED] TR03JA18.004

(h) Minimum Equipment List (MEL)

(1) Within 30 days after the effective date of this AD, amend the operator's ATR MEL, as applicable, by incorporating the dispatch restrictions listed in figure 2 to paragraph (h)(1) of this AD, and thereafter operate the airplane accordingly. BILLING CODE 4910-13-P [GRAPHIC] [TIFF OMITTED] TR03JA18.005

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BILLING CODE 4910-13-C
(2) Amending the operator's ATR MEL, as applicable, of an airplane by inserting a copy of this AD, or incorporating a later MMEL revision which includes the same dispatch restrictions as specified in figure 2 to paragraph (h)(1) of this AD is acceptable for compliance with the requirements of paragraph (h)(1) of this AD for that airplane.
(3) As of the effective date of this AD: If any of the systems identified in paragraph (h)(3)(i), (h)(3)(ii), and (h)(3)(iii) of this AD are inoperative, an airplane may be operated as specified in the MMEL, provided that the MEL of that airplane has been amended to be consistent with the MEL restrictions specified in figure 2 of this AD.
(i) One of two ADCs.
(ii) One of two AHRSs.
(iii) One of two DC generators.

(i) Optional Software Modification

Installation of new avionics suite standard 2 software on an airplane, in accordance with the Accomplishment Instructions of ATR Service Bulletin ATR42-31-0091, Revision 1, dated May 05, 2015, or ATR Service Bulletin ATR72-31-1092, Revision 2, dated March 31, 2015, as applicable, terminates the AFM and MEL revisions required by paragraphs (g) and (h) of this AD, for that airplane.

(j) Credit for Previous Actions

This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using ATR Service Bulletin ATR42-31-0091, dated December 17, 2014; or ATR Service Bulletin ATR72-31-1092, dated October 7, 2014, or Revision 1, dated December 9, 2014, as applicable.

(k) 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. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (l)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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 EASA; or ATR-GIE Avions de Transport R[eacute]gional's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA- authorized signature.

(l) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD

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2015-00237R1, dated December 16, 2015, for related information. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-1177.
(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 (m)(3) and (m)(4) of this AD.

(m) 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 todo the actions required by this AD, unless this AD specifies otherwise.
(i) ATR Service Bulletin ATR42-31-0091, Revision 1, dated May 05, 2015.
(ii) ATR Service Bulletin ATR72-31-1092, Revision 2, dated March 31, 2015.
(3) For service information identified in this AD, contact ATR- GIE Avions de Transport R[eacute]gional, 1, All[eacute]e Pierre Nadot, 31712 Blagnac Cedex, France; telephone +33 (0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; email aircraft.com">continued.airworthiness@atr-aircraft.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

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2015-00237R1, dated December 16, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI'') to correct an unsafe condition for certain ATR-GIE Avions de Transport R[eacute]gional Model ATR42-500 and ATR72-212A airplanes. The MCAI states:

During flight evaluations performed on Flight Synthetic Test Devices of ATR airplanes equipped with New Avionics Suite (also known as `Glass Cockpit'), with one Air Data Computer (ADC) or one Attitude and Heading Reference System (AHRS) inoperative, it was found that, after engine failure during autopilot (AP) or Yaw Damper (YD) re-engagement, the YD unit commanded the rudder to return to neutral position leading to inadequate balancing of the asymmetric power.
Subsequent flight tests confirmed the YD unit behavior observed during flight simulator evaluation and identified that a software issue is the root cause of this system reaction.
Additionally, it was identified that the failure of one of the Direct Current (DC) Generators with a concurrent shutdown of the opposite engine leads to loss of the AHRS#2 and ADC#2 and resulting in YD command the rudder into neutral position.
This condition, if not corrected, could result in loss of control of the airplane.
To address this potential unsafe condition EASA issued AD 2015- 0230 to introduce operational restrictions affecting in-flight use of AP and/or YD with an inoperative AHRS, or ADC and the relevant dispatch limitations.
Since that [EASA] AD was issued, it was determined that airplanes modified in service by incorporating New Avionics Suite Standard 2 are not affected and that the operation of an airplane with combination of inoperative ADC, AHRS and DC Generator items is allowed. Additional investigation has resulted in prohibiting theuse of AP or YD also in case of both engine operative, when an ADC or an AHRS becomes inoperative.
For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2015-0230, which is superseded, and introduces AP or YD operational restrictions applicable for dual engine operation.
This [EASA] AD is considered an interim action and further [EASA] AD action may follow.
This [EASA] AD is revised to specify the Reason leading to AD issuance.

Required actions also include AP or YD operational restrictions applicable for dual engine operation. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-1177.

Related Service Information Under 1 CFR Part 51

Avions de Transport R[eacute]gional has issued ATR Service Bulletin ATR42-31-0091, Revision 1, dated May 05, 2015; and ATR Service Bulletin ATR72-31-1092, Revision 2, dated March 31, 2015. The service information describes proceduresfor, among other things, modifying the software for the integrated avionics display (IAD), the core processing module (CPM), the switch module (SWM), and the flight warning main configuration file (FWMCF). These documents are distinct since they apply to different airplane models.
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.

FAA's Determination and Requirements of This AD

This product has been approved by the aviation authority of another

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country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs.

FAA's Determination of the Effective Date

There are currently no domestic operators of this product. Therefore, we find good cause that notice and opportunity for prior public comment are unnecessary. In addition, for the reason(s) stated above, we find that good cause exists for making this amendment effective in less than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2017-1177; Product Identifier 2015-NM-195-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received bythe closing date and may amend this AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD.

Costs of Compliance

Currently, there are no affected U.S.-registered airplanes. If an affected airplane is imported and placed on the U.S. Register in the future, we provide the following cost estimates to comply with this AD:
We estimate that it will take about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD will be $85 per product.
In addition, we estimate that the optional modification will take about 3 work-hours for a cost of $255 per product.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authorityto 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 accordance with 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 smallentities 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.