8160 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Proposed Rules 

as required by paragraphs (k)(2) and (k)(3) of 

this AD, terminates the inspections required 

by paragraph (g)(1) of this AD, provided the 

preventative modification is done before 

further flight after accomplishing an 

inspection required by paragraph (g) of this 

AD. 

(2) Replacing the crown skin panel 

between STA 297 and STA 439, S–4L to S– 

4R, using a method approved in accordance 

with the procedures specified in paragraph 

(m) of this AD, terminates the inspections 

required by paragraphs (g)(1), (g)(2), and 

(g)(3) of this AD. 

(k) Exceptions to Service Information 

Specifications and Preventative Modification 

(1) Where Boeing Special Attention Service 

Bulletin 757–53–0097, Revision 2, dated July 

28, 2015, specifies a compliance time ‘‘after 

the Revision 2 date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Boeing Special Attention Service 

Bulletin 757–53–0097, Revision 2, dated July 

28, 2015, specifies to contact Boeing for 

repair instructions: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (m) of this AD. 

(3) If any cracking is found during any 

inspection specified in paragraph (j)(1) of this 

AD, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (m) of this 

AD. 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for Zone 

1 inspections required by paragraph (g) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Special Attention Service Bulletin 

757–53–0097, dated November 22, 2010, 

which was incorporated by reference in AD 

2011–01–15, Amendment 39–16572 (76 FR 

1351, January 10, 2011). 

(2) This paragraph provides credit for the 

Zone 1 inspection required by paragraph (g) 

of this AD, if those actions were performed 

before the effective date of this AD, using 

Boeing Special Attention Service Bulletin 

757–53–0097, Revision 1, dated January 6, 

2011, which is not incorporated by reference 

in this AD. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (m)(1) of this AD. Information may 

be emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair. 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved the repair method, 

modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane and the approval must 

specifically refer to this AD. 

(4) AMOCs approved for AD 2011–01–15, 

Amendment 39–16572 (76 FR 1351, January 

10, 2011), are not approved as AMOCs for the 

corresponding provisions of paragraph (g) of 

this AD. 

(5) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (m)(5)(i) and (m)(5)(ii) apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(n) Related Information 

(1) For more information about this AD, 

contact Eric Schrieber, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office (ACO), 

3960 Paramount Boulevard, Lakewood, CA 

90712–4137; phone: 562–627–5348; fax: 562– 

627–5210; email: Eric.Schrieber@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, CA 90846–0001; 

telephone: 206–544–5000, extension 2; fax: 

206–766–5683; Internet https://

www.myboeingfleet.com. You may view this 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on February 

8, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03297 Filed 2–17–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0465; Directorate 

Identifier 2015–NM–096–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200 and –300 series 

airplanes; and Model A340–200 and 

–300 series airplanes. This proposed AD 

was prompted by a determination that 

the compliance times for certain postrepair inspections and certain allowable 

damage limits (ADLs) must be reduced 

in order to address fatigue. This 

proposed AD would require identifying 

any repairs and ADLs used to assess or 

control any structural damage on certain 

structural areas, and corrective action if 

necessary. We are proposing this AD to 

prevent fatigue damage on primary 

structure and structural repairs, which 

could result in reduced structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 4, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone: +33 5 61 93 

36 96; fax: +33 5 61 93 45 80; email: 

airworthiness.A330-A340@airbus.com; 

Internet: http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 


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Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

0465; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone: 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: 425–227–1138; 

fax: 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2016–0465; Directorate Identifier 

2015–NM–096–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

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– 

0101R1, dated June 12, 2015 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A330–200 and 

–300 series airplanes; and Model A340– 

200 and –300 series airplanes. The 

MCAI states: 

Result of a fleet survey accomplished in 

2008 identified that the nature of flight 

missions of A330 and A340–200/300 fleets 

had significantly changed in comparison 

with assumed usage during the type 

certification. Consequently, it was decided to 

recalculate the Structural Repair Manual 

(SRM) fatigue values to ensure that the given 

threshold and intervals remain valid. 

The results of this recalculation identified 

reduced thresholds and intervals applicable 

for repairs and Allowable Damage Limits 

(ADL) affecting the following areas: 

—Door cut-out corners of door surrounding 

panels (forward cargo door, forward 

passenger (PAX) door, mid PAX door, 

emergency exit door/PAX door 3, aft cargo 

door, bulk cargo door, aft PAX door), on 

both Left Hand (LH) and Right Hand (RH) 

sides, 

—Stringer (STGR) 9 junction between Frame 

(FR) 10 and FR13 on both LH and RH 

sides, and 

—Fuselage skin doubler repairs on both LH 

and RH sides. 

Failing to apply the reduced thresholds 

and intervals, could adversely affect the 

structural integrity of the aeroplane. 

To address this unsafe condition, Airbus 

issued SRM revision dated April 2013 and 

temporary revision (TR) 53–001 for the 

STGR9 junction between FR10 and FR13 area 

(and subsequent revisions) to introduce 

reduced thresholds and intervals for the 

affected ADLs and repairs and issued a set of 

Service Bulletins (SB) to identify the ADLs 

used and repairs made, as well as to enable 

operators to update aeroplane repair records. 

Consequently EASA issued AD * * *, to 

require identification of any repairs and/or 

ADL used to assess or control any structural 

damage on certain structural areas and, 

depending on findings, accomplishment of 

corrective action(s) [including revising the 

maintenance or inspection program as 

applicable to incorporate revised thresholds 

and intervals and repair]. 

Since that [EASA] AD was issued, data 

review confirmed that A330 freighter 

versions are not affected by the unsafe 

condition. 

This [EASA] AD is revised to remove 

A330–223F and A330–243F from the 

Applicability. 

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– 

0465. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. The service 

information describes procedures for 

updating the airplane repair records 

with revised thresholds and intervals. 

• Airbus Service Bulletin A330–53– 

3232, dated November 4, 2014. 

• Airbus Service Bulletin A330–53– 

3233, dated September 26, 2014. 

• Airbus Service Bulletin A330–53– 

3234, dated December 8, 2014. 

• Airbus Service Bulletin A330–53– 

3235, Revision 01, dated January 14, 

2015. 

• Airbus Service Bulletin A340–53– 

4222, dated November 25, 2014. 

• Airbus Service Bulletin A340–53– 

4223, dated September 26, 2014. 

• Airbus Service Bulletin A340–53– 

4224, dated December 15, 2014. 

• Airbus Service Bulletin A340–53– 

4225, Revision 01, dated January 14, 

2015. 

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 Proposed AD 

This product has been approved by 

the aviation authority of another 

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 proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 95 airplanes of U.S. registry. We 

also estimate that it would take about 2 

work-hours per product to comply with 

the basic requirements of this proposed 

AD. The average labor rate is $85 per 

work-hour. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $16,150, or $170 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

Authority for This Rulemaking 

Title 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 


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that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2016–0465; 

Directorate Identifier 2015–NM–096–AD. 

(a) Comments Due Date 

We must receive comments by April 4, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD; 

manufacturer serial numbers (MSNs) 1 

through 1,600 inclusive. 

(1) Airbus Model A330–201, –202, –203, 

–223, –243, –301, –302, –303, –321, –322, 

–323, –341, –342, and –343 airplanes. 

(2) Airbus Model A340–211, –212, –213, 

–311, –312, and –313 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a determination 

that the compliance times for certain postrepair inspections and certain allowable 

damage limits (ADLs) must be reduced in 

order to address fatigue. We are issuing this 

AD to prevent fatigue damage on primary 

structure and structural repairs, which could 

result in reduced structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Records Review 

At the applicable times in table 1 to 

paragraph (g) of this AD, review the airplane 

maintenance records to identify any 

structural repair manual (SRM) ADLs used to 

assess or control any structural damage or 

any structural repair accomplished as 

specified in an SRM, as applicable, that have 

been applied on the areas as specified in 

table 2 to paragraph (g) of this AD. 

TABLE 1 TO PARAGRAPH (g) OF THIS AD—COMPLIANCE TIMES

Affected airplanes ADL location/repair Compliance time Related Service Bulletin 

A330–200 Pre-mod 49144 ............ Mid passenger (PAX) door surround panels.Within 12 months after the effective date of this AD.Airbus Service Bulletin A330–53– 

3232, dated November 4, 2014. 

A330–200 Pre-mod 49144 ............ Forward cargo door, emergency 

exit door/PAX door 3, aft cargo 

door, bulk cargo door, and aft 

PAX door surround panels.

Within 24 months after the effective date of this AD.Airbus Service Bulletin A330–53– 

3232, dated November 4, 2014. 

A330–300 Pre-mod 49144 and 

A340–200/–300 pre-mod 49144.

Mid PAX door surround panels, 

forward cargo door, emergency 

exit door/PAX door 3, aft cargo 

door, bulk cargo door, and aft 

PAX door surround panels.

Within 24 months after the effective date of this AD.Airbus Service Bulletin A330–53– 

3232, dated November 4, 2014 

or Airbus Service Bulletin 

A340–53–4222, dated November 25, 2014. 

All, Post-mod 40347 ...................... Forward PAX door surround panels with an ADL with a Temporary Life Limit.Within 12 months after the effective date of this AD.Airbus Service Bulletin A330–53– 

3233, dated September 26, 

2014 or Airbus Service Bulletin 

A340–53–4223, dated September 26, 2014. 

All, Post-mod 40347 ...................... Forward PAX door surround panels with an ADL with a Permanent Acceptance.Within 24 months after the effective date of this AD.Airbus Service Bulletin A330–53– 

3233, dated September 26, 

2014 or Airbus Service Bulletin 

A340–53–4223, dated September 26, 2014. 

All ................................................... STGR9 junction between frame 

(FR) 10 and FR13.

Within 12 months after the effective date of this AD.Airbus Service Bulletin A330–53– 

3235, Revision 01, dated January 14, 2015 or Airbus Service 

Bulletin A340–53–4225, Revision 01, dated January 14, 

2015. 

A340–200/–300 Weight Variant 

(WV)00s.

Forward and rear fuselage ........... Within 12 months after the effective date of this AD.Airbus Service Bulletin A340–53– 

4224, dated December 15, 

2014. 

A340–200/–300 WV00s ................. Nose forward and center fuselage Within 24 months after the effective date of this AD.Airbus Service Bulletin A340–53– 

4224, dated December 15, 

2014. 


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TABLE 1 TO PARAGRAPH (g) OF THIS AD—COMPLIANCE TIMES—Continued 

Affected airplanes ADL location/repair Compliance time Related Service Bulletin 

A330–200/–300 pre-MOD 49144 

and A340–200/–300 WV20s.

Forward and rear fuselage, nose 

forward and center fuselage.

Within 24 months after the effective date of this AD.Airbus Service Bulletin A330–53– 

3234, dated December 8, 2014 

or Airbus Service Bulletin 

A340–53–4224, dated December 15, 2014. 

A330–200/–300 post-MOD 49144 

and A340–200/–300 post-MOD 

49144.

Nose forward and center fuselage Within 24 months after the effective date of this AD.Airbus Service Bulletin A330–53– 

3234, dated December 8, 2014 

or Airbus Service Bulletin 

A340–53–4224, dated December 15, 2014. 

TABLE 2 TO PARAGRAPH (g) OF THIS AD—AFFECTED AREAS

Affected areas (on both left-hand and right-hand sides) As specified in Airbus Service Bulletin— 

Door cut-out corners of door surrounding panels (forward cargo door, 

mid PAX door, emergency exit door/PAX door 3, aft cargo door, bulk 

cargo door, aft PAX door).

A330–53–3232, dated November 4, 2014 (for Model A330 series airplanes) or A340–53–4222, dated November 25, 2014 (for Model 

A340 series airplanes). 

Forward PAX door surround panels ......................................................... A330–53–3233, dated September 26, 2014 (for Model A330 series airplanes) or A340–53–4223, dated September 26, 2014 (for Model 

A340 series airplanes). 

Fuselage skin doubler repairs .................................................................. A330–53–3234, dated December 8, 2014 (for Model A330 series airplanes) or A340–53–4224, dated December 15, 2014 (for Model 

A340 series airplanes). 

STGR9 junction between FR10 and FR13 .............................................. A330–53–3235, Revision 01, dated January 14, 2015 (for Model A330 

series airplanes) or A340–53–4225, Revision 01, dated January 14, 

2015 (for Model A340 series airplanes). 

(h) Corrective Actions 

If, during any review required by 

paragraph (g) of this AD, it is determined that 

an SRM ADL was used on an area specified 

in table 2 to paragraph (g) of this AD to assess 

or control any structural damage, or any 

structural repair of an area specified in table 

2 to paragraph (g) of this AD was 

accomplished as specified in the instructions 

of the applicable SRM revision, dated before 

April 2013 or SRM temporary revision (TR) 

dated before November 28, 2014: Within the 

applicable compliance time specified in table 

1 to paragraph (g) of this AD, do the actions 

specified in paragraph (h)(1) or (h)(2) of this 

AD, as applicable. 

(1) Revise the maintenance or inspection 

program, as applicable, with the applicable 

revised thresholds and intervals for the 

identified structural repairs embodied on the 

airplane, and accomplish all updated 

inspections, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

table 2 to paragraph (g) of this AD, except as 

required by paragraphs (h)(1)(i) and (h)(1)(ii) 

of this AD. 

(i) Where the applicable Airbus service 

information identified in table 2 to paragraph 

(g) of this AD specifies to contact Airbus for 

specific assessment, revise the maintenance 

or inspection program and accomplish all 

updated inspections, as applicable, using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

(ii) Where the Airbus applicable service 

information identified in table 2 to paragraph 

(g) of this AD specifies ‘‘current SRM,’’ no 

SRM revision dated before April 2013 or 

SRM TR dated before November 28, 2014, is 

considered a ‘‘current SRM.’’ 

(2) For any repair that was previously 

allowed in any revision of the Airbus A330 

or A340 SRM, as applicable, dated before 

April 2013; or in any SRM TR dated before 

November 28, 2014, to the applicable SRM: 

Make an assessment using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the EASA; or Airbus’s 

EASA DOA and perform necessary corrective 

actions at the applicable times identified 

therein. 

(i) Limitation on Repair/Replacement 

As of the effective date of this AD, for any 

structural damage in the areas identified in 

table 2 to paragraph (g) of this AD that has 

exceeded the ADL, no repair or replacement 

may be done using an Airbus A330 or A340 

SRM dated before April 2013, or any SRM TR 

dated before November 28, 2014. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–1138; fax: 425–227– 

1149. 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. The AMOC 

approval letter must specifically reference 

this AD. 

(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 Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraphs (h)(1)(i), (h)(1)(ii), 

and (h)(2) of this AD: If any service 

information contains procedures or tests that 

are identified as RC, those procedures and 

tests must be done to comply with this AD; 

any procedures or tests that are not identified 

as RC are recommended. Those procedures 

and tests that are not identified as RC may 

be deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the 

procedures and tests identified as RC can be 

done and the airplane can be put back in an 

airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 


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2015–0101R1, dated June 12, 2015, 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–2016–0465. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone: +33 

5 61 93 36 96; fax: +33 5 61 93 45 80; email: 

airworthiness.A330-A340@airbus.com; 

Internet: http://www.airbus.com. You may 

view this service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on February 

6, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03137 Filed 2–17–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0463; Directorate 

Identifier 2015–NM–155–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all The 

Boeing Company Model 777 airplanes. 

This proposed AD was prompted by a 

report of an incident involving a landing 

in which the pilots needed to input 

corrections due to airplane yaw and roll 

to the right; the main landing gear 

(MLG) aft trunnion pin was later found 

to be fractured. This proposed AD 

would require identification and 

replacement of certain MLG aft trunnion 

pins. We are proposing this AD to 

prevent a fractured MLG aft trunnion 

pin, which could result in collapse of 

the MLG and consequent loss of control 

of the airplane during landing. 

DATES: We must receive comments on 

this proposed AD by April 4, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone: 

206–544–5000, extension 1; fax: 206– 

766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

0463. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

0463; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6513; 

fax: 415–917–6590; email: 

Narinder.Luthra@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2016–0463; Directorate Identifier 2015– 

NM–155–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of 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 proposed AD. 

Discussion 

We have received a report of an 

incident involving a landing in which 

the pilots needed to input corrections 

due to airplane yaw and roll to the right; 

the MLG aft trunnion pin was later 

found to be fractured. Other damage 

included minor damage to the gear 

beam and trunnion door panel and a 

broken tie rod. Analysis of the fractured 

pin showed that the crack started from 

an area of heat damage introduced 

during manufacturing. A review of gear 

overhaul records indicated that other 

pins manufactured by the same supplier 

had similar signs of heat damage, 

suspected to have been caused by 

abusive chrome grinding. This evidence 

suggests that the heat damage occurred 

during manufacturing, so it is possible 

that other airplanes have aft trunnion 

pins with similar heat damage. This 

condition, if not corrected, could result 

in collapse of the MLG and consequent 

loss of control of the airplane during 

landing. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 777–32A0103, Revision 1, 

dated December 10, 2015. The service 

information describes procedures for 

identifying and replacing certain MLG 

aft trunnion pins. 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 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 


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