AD 2004-25-21

This amendment adopts a new airworthiness directive (AD), applicable to certain Model EMB-135 and -145 series airplanes. This AD requires modification of the pitch trim system, which includes replacing certain components of the system with new or serviceable components, and upgrading certain software to a newer version. This action is necessary to prevent the temporary loss of the pitch trim command, which could result in reduced controllability of the airplane and consequent injury to the flightcrew and passengers. This action is intended to address the identified unsafe condition.

Final rule.

2004-25-21 Empresa Brasileira de Aeronautica S.A. (EMBRAER): Amendment 39-13909. Docket 2003-NM-97-AD.

Applicability: Model EMB-135 and -145 series airplanes, as listed in EMBRAER Service Bulletin 145LEG-27-0002, Revision 01, dated April 15, 2003; EMBRAER Service Bulletin 145-27-0084, Revision 04, dated October 21, 2003; and EMBRAER Service Bulletin 145-27- 0096, Revision 03, dated September 2, 2003; certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent the temporary loss of the pitch trim command, which could result in reduced controllability of the airplane and consequent injury to the flightcrew and passengers, accomplish the following:

Prior or Concurrent Requirements

(a) Prior to the accomplishment of the actions in paragraph (b) of this AD, accomplish any applicable prior or concurrent requirement listed in paragraph (a)(1) or (a)(2) of this AD.

(1) For airplanes listed in EMBRAER Service Bulletin 145-31- 0020, Change 03, dated July 30, 2002, that are equipped with engine indicating and crew alerting system/electronic flight information system (EICAS/EFIS) software version 16.5 or earlier: Upgrade to software version 17 of the EICAS/EFIS software, in accordance with the Accomplishment Instructions of the service bulletin.

(2) For airplanes listed in EMBRAER Service Bulletin 145-27- 0083, Change 04, dated November 27, 2002: Install electrical provisions for the new pitch trim system in accordance with the Accomplishment Instructions of the service bulletin.

Modification of the Pitch Trim System: Replacement, Installation, and Connection

(b) Within 18 months or 5,000 flight hours after the effective date of this AD, whichever occurs first, but following any applicable prior or concurrent requirement listed in paragraph (a)(1) or (a)(2) of this AD: Modify the pitch trim system for the affected airplanes by accomplishing the actions in paragraphs (b)(1), (b)(2), (b)(3), (b)(4), (b)(5), (b)(6), and (b)(7), as applicable. Accomplish the actions in the sequence specified in this AD.

(1) For all airplanes: Replace the horizontal stabilizer control unit (HSCU) with a new unit with improved features, and having a new part number, in accordance with paragraph 3.J. (Part I) of EMBRAER Service Bulletin 145LEG-27-0002, Revision 01, dated April 15, 2003 (for Model EMB-135BJ series airplanes); or paragraph 3.J. (Part I) of EMBRAER Service Bulletin 145-27-0084, Revision 04, dated October 21, 2003 (for Model EMB-135ER, -135LR, -135KE, and -135KL series airplanes; and Model EMB-145, -145ER, -145MR, -145LR, -145XR, - 145MP, and -145EP series airplanes); as applicable.

(2) For airplanes listed in EMBRAER Service Bulletin 145-27- 0091, Change 02, dated November 27, 2002: Replace the horizontal stabilizer actuator (HSA) with a new HSA having a new part number in accordance with the Accomplishment Instructions of the service bulletin.

(3) For airplaneslisted in EMBRAER Service Bulletin 145-31- 0028, Change 04, dated December 20, 2002: Replace the aural warning unit (AWU) with an AWU having improved features and a new part number in accordance with the Accomplishment Instructions of the service bulletin.

Note 1: EMBRAER Service Bulletin 145-31-0028 references Grimes Aerospace Company Service Bulletin 80-0694-33-SB01, dated January 1, 2002, as an additional source of service information for accomplishment of the replacement. The Grimes Aerospace service bulletin is included in the EMBRAER service bulletin.

(4) Replace the IC-600 units in accordance with paragraph (b)(4)(i) or (b)(4)(ii) of this AD.

(i) For airplanes listed in EMBRAER Service Bulletin 145LEG-31- 0001, dated August 19, 2002 (for Model EMB-135BJ series airplanes); or EMBRAER Service Bulletin 145-31-0033, Revision 03, dated August 25, 2003 (for Model EMB-135ER, -135LR, -135KE, and -135KL series airplanes; and Model EMB-145, -145ER, -145MR, -145LR, -145XR,- 145MP, and -145EP series airplanes): Replace any IC-600 units having part numbers (P/N) 7107000-82407, -82407 MODS-B, -82427, -83407, and -83407 MODS-B, with new IC-600 MOD AB units having P/Ns 7107000- 82428 or -83428, as applicable; and install a new software version 18.5 (phase 8.5) of the EICAS/EFIS system for all IC-600 MOD AB hardware. Accomplish the actions in accordance with the Accomplishment Instructions of the applicable service bulletin.

(ii) For airplanes listed in EMBRAER Service Bulletin 145-31- 0042, Revision 01, dated January 7, 2004: Replace any IC-600 units having P/N 7107000-82428 and -82438 with new IC-600 units having P/ Ns 7017000-82430 or -83430, in accordance with EMBRAER Service Bulletin 145-31-0042, Revision 01, dated January 7, 2004, or Revision 02, dated June 23, 2004. Prior to or concurrently with the actions specified in Revision 01 or 02 of EMBRAER Service Bulletin 145-31-0042, remove or replace certain placards in the cockpit in accordance with the Accomplishment Instructions of EMBRAER Service Bulletin 145-25-0210, dated March 30, 2001; and modify and re- identify the central maintenance computer in accordance with the Accomplishment Instructions of EMBRAER Service Bulletin 145-45-0003, dated July 5, 2000.

Note 2: EMBRAER Service Bulletins 145LEG-31-0001 and 145-31-0033 reference Honeywell Service Bulletin 7017000-22-6089, Revision 003, dated October 16, 2003, as an additional source of service information for accomplishment of the replacement and installation. EMBRAER Service Bulletin 145-31-0042 references Honeywell Service Bulletin 7017000-22-6102, dated November 25, 2003, as an additional source of service information for accomplishment of the replacement with P/Ns 7017000-82430 or -83430.

(5) For airplanes listed in EMBRAER Service Bulletin 145LEG-27- 0004, dated January 21, 2003 (for Model EMB-135BJ series airplanes); or EMBRAER Service Bulletin 145-27-0096, Revision 03, dated September 2, 2003 (for Model EMB-135ER, -135LR, -135KE, and -135KL series airplanes; and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP series airplanes): Replace the control yoke pitch trim switch with a new switch having a new part number; and replace the placard around the switch knob, as applicable, with a new placard having a new part number in accordance with the Accomplishment Instructions of the applicable service bulletin.

(6) For airplanes listed in EMBRAER Service Bulletin 145-27- 0073, Change 02, dated February 26, 2002: Replace the pitch trim back-up control switch with a new switch having a new part number (including reidentifying the trim control panel) in accordance with the Accomplishment Instructions of the service bulletin.

(7) For all airplanes: Connect the HSCU and the data acquisition unit (DAU) (including the replacement of the pitch trim system circuit breakers with new circuit breakers sized for the new system load capacity, as applicable) in accordance with paragraph 3.K. (Part II) of EMBRAER Service Bulletin 145LEG-27-0002, Revision 01, dated April 15, 2003 (for Model EMB-135BJ series airplanes); or paragraphs 3.K., 3.L., 3.M., and 3.N. (Parts II, III, IV, and V) of EMBRAER Service Bulletin 145-27-0084, Revision 04, dated October 21, 2003 (for Model EMB-135ER, -135LR, -135KE, and -135KL series airplanes; and Model EMB-145, -145ER, -145MR, -145LR, -145XR, - 145MP, and -145EP series airplanes).

Parts Installation

(c) As of the effective date of this AD, no person may install, on any airplane, a part unless it has been modified in accordance with the applicable paragraph of the affected service bulletins listed in Table 1 of this AD.

Table 1.--Parts Installation Paragraphs

EMBRAER service bulletin
Parts installation paragraph
145-27-0084, Revision 04, dated October 21, 2003
1.C.(1)(a).
145LEG-27-0002, Revision 01, dated April 15, 2003
1.C.(1)(a).
145-27-0091, Change 02, dated November 27, 2002
1.C.(1)(a).
145-31-0028, Change 04, dated December 20, 2002
1.C.(a).
145-31-0033, Revision 03, dated August 25, 2003
1.C.(1).

Actions Accomplished Previously in Accordance With Certain Service Bulletins

(d) Actions accomplished before the effective date of this AD in accordance with the service bulletins listed in Table 2 of this AD are considered acceptable for compliance with the corresponding actions specified in this AD.

Table 2.--Previous Issues of Service Bulletins

EMBRAER service bulletin
Change/revision level
Date
145-27-0083
Original
October 4, 2001.
145-27-0083
01
March 15, 2002.
145-27-0083
02
April 11, 2002.
145-27-0083
03
July 16, 2002.
145-27-0084
01
December 20, 2002.
145-27-0084
02
February 25, 2003.
145-27-0084
03
July 15, 2003.
145-27-0096
01
April 7, 2003.
145-27-0096
02
July 1, 2003.
145-31-0028
Original
December 13, 2001.
145-31-0028
01
January 22, 2002.
145-31-0028
02
April 2, 2002.
145-31-0028
03
August 22, 2002.
145-31-0033
02
April 17, 2003.
145LEG-27-0002
Original
February 5, 2003.

Alternative Methods of Compliance

(e) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, is authorized to approve alternative methods of compliance for this AD.

Incorporation by Reference

(f) Unless otherwise specified in this AD, the actions shall be done in accordance with the service bulletins in Table 3 of this AD.

Table 3.--Material Incorporated by Reference

EMBRAER service bulletin
Page No.
Change/revision level
Date
145-25-0210
1-12
Original
March 30, 2001.

145-27-0073
1, 2
3, 4
5-9
02
01
Original
February 26, 2002.
August 29, 2000.
June 30, 2000.

145-27-0083
1, 2
3-8, 15-30, 33-54
9-12
13, 14, 31, 32
04
01
03
02
November 27, 2002.
March 15, 2002.
July 16,2002.
April 11, 2002.

145-27-0084
1-4, 6, 11, 12, 15
5, 7-10, 13, 14, 16 40
04
03
October 21, 2003.
July 15, 2003.

145-27-0091
1, 2
3-11
02
Original
November 27, 2002.
February 8, 2002.

145-27-0096
1-2
3, 5-8, 12, 14, 15, 17-22
4, 13, 16
9-11
03
Original
02
01
September 2, 2003.
December 18, 2002.
July 1, 2003.
April 7, 2003.
145-31-0020
1-81
03
July 30, 2002.
145-31-0028
1-17
04
December 20, 2002.

145-31-0033
1-5, 9-11, 15, 16, 21-24, 56-58
6-8, 12-14, 17-20, 25-55, 59
03
02
August 25, 2003.
April 17, 2003.
145-31-0042
1-114
01
January 7, 2004.

145-31-0042
1-10, 21-24, 99, 100
11-20, 25-98, 101-114
02
01
June 23, 2004.
January 7, 2004.

145LEG-27-0002
1, 5
2-4, 6-15
01
Original
April 15, 2003.
February 5, 2003.
145-45-0003
1-15
Original
July 5, 2000.
145LEG-27-0004
1-16
Original
January 21, 2003.
145LEG-31-0001
1-12
Original
August 19, 2002.

This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Empresa Brasileira de Aeronautica S.A. (EMBRAER), PO Box 343--CEP 12.225, Sao Jose dos Campos--SP, Brazil. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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/code_of_federal_regulations/ibr_locations.html .

Note 3: The subject of this AD is addressed in Brazilian airworthiness directive 2003-03-01, dated April 3, 2003.

Effective Date

(g) This amendment becomes effective on January 26, 2005.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Model EMB-135 and -145 series airplanes was published in the Federal Register on February 6, 2004 (69 FR 5759). That action proposed to require modification of the pitch trim system, which includes replacing certain components of the system with new or serviceable components, and upgrading certain software to a newer version.

Comments

Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received.

Request To Include New Revision of Service Bulletin 145-31-0042

One commenter requests that we use EMBRAER Service Bulletin 145-31- 0042, Revision 01, dated January 7, 2004, as the appropriate source of service information for replacing certain integrated computers (IC) in paragraph (b)(4) of the proposed AD. The commenter states that the ICs in this service bulletin are upgrades, and classified as optional replacements for the IC-600 computers referenced in EMBRAER Service Bulletin 145-31-0033, Revision 03, dated August 25, 2003, which is the appropriate source of service information for replacing certain IC-600 computers per paragraph (b)(4) of the proposed AD.

We partially agree with the commenter's request. We agree that EMBRAER Service Bulletin 145-31-0042, Revision 01, may be used as an optional source of service information for doing the actions in paragraph (b)(4)
of the AD. Additionally, the manufacturer has also issued Revision 02, dated June 23, 2004, and it may also be used as an optional source of service information. Since these revisions are not the only source of appropriate service information, operators may still choose to do the replacement in accordance with the service information in the proposed AD. Therefore, we have revised paragraph (b)(4) of this final rule to include EMBRAER Service Bulletin 145-31-0042, Revision 01 and Revision 02, as sources of service information for operators of airplanes listed in that service bulletin to choose as an optional way to replace the IC-600 computers as proposed in paragraph (b)(4). This optional replacement includes reidentifying IC-600 1 and IC-600 2, and loading a new configuration file to the IC-600 1 and IC-600 2 configuration modules.

EMBRAER Service Bulletin 145-31-0042 references Honeywell Service Bulletin 7017000-22-6102, dated November 25, 2003, as an additional source of service information for accomplishing the upgrade and re- identification. EMBRAER Service Bulletin 145-31-0042 also contains other procedures that are not applicable to the IC-600 upgrade, but these actions are not required by this final rule.

EMBRAER Service Bulletin 145-31-0042 specifies that the following service bulletins must be accomplished previously, as applicable, on the airplanes listed in these service bulletins:

EMBRAER Service Bulletin 145-31-0020, Change 03, dated July 30, 2002, which contains procedures for replacing the IC-600 1 and IC-600 2, and the data acquisition unit (DAU); and for upgrading the engine indicating and crew alerting system (EICAS) to version 17.

EMBRAER Service Bulletin 145-25-0210, dated March 30, 2001, which describes procedures for removing and/or replacing certain placards in the cockpit. These placards are related to the EICAS.

EMBRAER Service Bulletin 145-45-0003, dated July 5, 2000, which describes procedures for modifying and re-identifying the central maintenance computer (CMC). This service bulletin refers to Vibro-Meter Service Bulletin 145-45-0503, dated March 20, 2000, as an additional source of service information for modifying and re-identifying the CMC. The Vibro-Meter service bulletin is included with EMBRAER Service Bulletin 145-45-0003.

Request To Include New Revision of Service Bulletin 145LEG-27-0002

Another commenter requests that we refer to EMBRAER Service Bulletin 145LEG-27-0002, Revision 01, dated April 15, 2003, as the appropriate source of service information for accomplishing the actions in paragraphs (b)(1) and (b)(7) of the proposed AD on Model EMB-135BJ series airplanes. The commenter advises that this is the latest revision of the service bulletin with the most current information.

We agree with the commenter. The new revision of the service bulletin identifies two new and improved horizontal stabilizer control units (HSCU), and reduces the number of airplanes to which this service bulletin applies. We have revised the applicability section, paragraphs (b)(1) and (b)(7), and Table 1 of the final rule to include references to EMBRAER Service Bulletin 145LEG-27-0002, Revision 01. We have also revised Table 2 of the final rule to include a reference to the original issue of EMBRAER Service Bulletin 145LEG-27-0002, dated February 5, 2003. EMBRAER Service Bulletin 145LEG-27-0002is applicable to Model EMB-135BJ series airplanes, and describes procedures for replacing the HSCU with a new unit having improved features. This service bulletin also describes procedures for connecting the HSCU and the DAU (including the replacement of the pitch trim system circuit breakers with new circuit breakers sized for the new system load capacity, as applicable).

Request To Extend Compliance Time

One commenter, an airplane operator, requests that the compliance time for accomplishing the seven actions in paragraph (b) of the proposed AD be extended to better accommodate the commenter's existing maintenance program. The compliance time, as proposed, is: "Within 18 months or 5,000 flight hours after the effective date of this AD, whichever occurs first." The commenter requests that the statement be revised to say, "Within 18 months or 5,000 flight hours after the effective date of this AD, whichever occurs later," or, "Within 36 months or 5,000 flight hours after the effective date of this AD, whichever occurs first." The commenter states that 5,000 flight hours work better with its existing maintenance program, and that 36 months is approximately equivalent to 5,000 flight hours for its operation. The commenter requests the extension in order to comply with the requirements of the proposed AD in a smooth and effective manner, and to reduce the time and effort to the commenter and the FAA in requesting and addressing alternative methods of compliance (AMOCs).

We do not agree with the commenter's request to extend the compliance time. The commenter provides no technical justification that extending the compliance time will still maintain an appropriate level of safety. In developing an appropriate compliance time for this proposed AD, we considered safety issues as well as the recommendations of the manufacturer and the Departmento de Aviacao Civil, (which is the airworthiness authority for Brazil), the availability of necessary parts, and the practical aspects of accomplishing the required actions within an interval of time that corresponds to the normal maintenance schedules of most affected operators. We do not find it necessary to change this proposal in this regard; however, the commenter still may apply for approval of an AMOC to extend the compliance time.

Request To Shorten Compliance Time

Another commenter supports the proposal and requests that the compliance time for accomplishing the proposed actions be shortened substantially. The commenter states that the unsafe condition is severe enough to warrant a more immediate compliance time. In addition, the commenter understands that the parts necessary to complete the modification are readily available and, therefore, the parts should be available to accomplish the proposed actions more quickly.

We do not agree that the unsafe condition is severe enough to justify shortening the compliance time substantially. The proposed compliance time was determined tobe appropriate in consideration of the safety implications, the average utilization rate of the affected fleet, the practical aspects of modifications during regular maintenance periods, and the availability of required modification parts. We do agree with the commenter that parts are available to accomplish the actions in the allotted time in the original NPRM. We have not revised the proposal to shorten the compliance time.

Request To Remove "Interim Action"

Another commenter, the airplane manufacturer, requests that we remove the section of the NPRM that describes this proposal as "interim action." The commenter states that the corrective action in the proposal completely addresses the specific unsafe conditions identified during the development of the Brazilian airworthiness directive
and the FAA NPRM. In addition, the commenter states that recent pitch trim failures induced by airspeed miscompares will be addressed by a new HSCU that is under development. Therefore, the commenter believes that it is not appropriate to label this proposal as "interim action."

We agree that the NPRM was issued to correct the stated known unsafe condition. In stating that the proposal is "interim action," we are advising the public that rulemaking on this subject may be issued in the future. This additional rulemaking could include a new HSCU that is under development. We have not changed the proposal to remove the reference to "interim action."

Conclusion

After careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the changes described previously. The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD.

Cost Impact

There are approximately 365 airplanes of U.S. registry affected by this AD.

For all affected airplanes, we estimate that it will takeapproximately 1 work hour per airplane to replace the HSCU, and that the average labor rate is $65 per work hour. The manufacturer will provide replacement parts at no cost. Based on these figures, the cost impact of this replacement on U.S. operators is estimated to be $23,725, or $65 per airplane.

For airplanes subject to EMBRAER Service Bulletin 145-27-0091, we estimate that it will take approximately 6 work hours per airplane to replace the horizontal stabilizer actuator, and that the average labor rate is $65 per work hour. The manufacturer will provide replacement parts at no cost. Based on these figures, the cost impact of this replacement is estimated to be $390 per airplane.

For airplanes subject to EMBRAER Service Bulletin 145-31-0028, we estimate that it will take approximately 2 work hours per airplane to replace the aural warning unit, and that the average labor rate is $65 per work hour. Required parts will cost approximately $1,100 per airplane. Based on thesefigures, the cost impact of this replacement is estimated to be $1,230 per airplane.

For airplanes subject to EMBRAER Service Bulletin 145LEG-31-0001 or 145-31-0033; or on which the optional action in EMBRAER Service Bulletin 145-31-0042 is done, we estimate that it will take between 1 and 6 work hours per airplane to install the new EICAS/electronic flight information system, and that the average labor rate is $65 per work hour. Required parts will cost between $10 and $25 per airplane. Based on these figures, the cost impact of this action is estimated to be between $75 and $415 per airplane.

For airplanes subject to EMBRAER Service Bulletin 145LEG-27-0004 or 145-27-0096, we estimate that it will take between 4 and 5 work hours per airplane to replace the yoke pitch trim switch, and that the average labor rate is $65 per work hour. Required parts will cost between $1,042 and $1,056 per airplane. Based on these figures, the cost impact of this action is estimated to be between $1,302 and $1,381 per airplane.

For airplanes subject to EMBRAER Service Bulletin 145-27-0073, we estimate that it will take approximately 3 work hours per airplane to replace the pitch trim back-up control switch, and that the average labor rate is $65 per work hour. Required parts will cost approximately $371 per airplane. Based on these figures, the cost impact of this replacement is estimated to be $566 per airplane.

For airplanes subject to the requirements in EMBRAER Service Bulletin 145-27-0083, we estimate that it will take approximately 38 hours to accomplish the modifications, and that the average labor rate is $65 per work hour. Required parts will cost approximately $448. Based on these figures, the cost impact of these modifications is estimated to be $2,918 per airplane.

For airplanes subject to the requirements in EMBRAER Service Bulletin 145-31-0020, we estimate that it will take between 9 and 56 hours to accomplish the proposed upgrade, and that theaverage labor rate is $65 per work hour. Required parts will cost between $3 and $5,100. Based on these figures, the cost impact of this action is estimated to be approximately between $588 and $8,740 per airplane.

For all affected airplanes, we estimate that it will take between 1 and 3 hours per airplane to accomplish the connection between the HSCU and the DAU specified in EMBRAER Service Bulletin 145LEB-27-0002, and that the average labor rate is $65 per work hour. Required parts will cost between $3 and $52 per airplane. Based on these figures, the cost impact of this action is estimated to be between $24,820 and $90,155, or between $68 and $247 per airplane.

The cost impact figures discussed above are based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.

Regulatory Impact

The regulations adopted herein 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132.

For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial numberof small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

39.13 [Amended]

2. Section 39.13 is amended by adding the following new airworthiness directive: