Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations 1497 

KS 67209; phone: 316–946–4142; fax: 316– 

946–4107; email: paul.devore@faa.gov. 

(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 to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Advanced Aircraft Extinguishers Service 

Bulletin TFA10–26–0020, Revision IR, dated 

January 12, 2015. 

(ii) Reserved. 

(3) For service information identified in 

this AD, 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. 

(4) You may view this service information 

at 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. 

(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/ibrlocations.html. 

Issued in Renton, Washington, on 

December 28, 2015. 

Philip Forde, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00004 Filed 1–12–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0937; Directorate 

Identifier 2014–NM–024–AD; Amendment 

39–18348; AD 2015–25–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2011–24– 

05 for certain Airbus Model A330–201, 

–202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and 

–343 airplanes, and Model A340–200 

and –300 series airplanes. AD 2011–24– 

05 required repetitive inspections for 

cracking of the hole(s) of the horizontal 

flange of the keel beam, and repair if 

necessary. This new AD requires 

changing the inspection compliance 

times, and, for certain airplanes, adding 

a one-time ultrasonic inspection for 

cracking at a certain fastener hole. This 

new AD also provides optional 

terminating action for the repetitive 

inspections. This AD was prompted by 

a determination that the rototest 

inspection and applicable corrective 

actions of a certain fastener hole were 

inadvertently omitted from the 

requirements in AD 2011–24–05. We are 

issuing this AD to detect and correct 

cracking of the fastener holes, which 

could result in rupture of the keel beam, 

and consequent reduced structural 

integrity of the airplane. 

DATES: This AD becomes effective 

February 17, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 17, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of January 3, 2012 (76 FR 

73496, November 29, 2011). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of September 13, 2007 (72 FR 

44731, August 9, 2007). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0937; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this final rule, 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 

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–2015– 

0937. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011). AD 2011–24–05 

applied to certain Airbus Model A330– 

201, –202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and 

–343 airplanes; and Model A340–200 

and –300 series airplanes. The NPRM 

published in the Federal Register on 

May 4, 2015 (80 FR 25249). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0010R1, dated May 5, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Airbus 

Model A330–201, –202, –203, –223, 

–243, –301, –302, –303, –321, –322, 

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

and Model A340–200 and –300 series 

airplanes. The MCAI states: 

During A330 and A340 aeroplanes fatigue 

tests, cracks were detected on the RH [righthand] and LH [left-hand] sides between the 

crossing area of the keel beam fitting and the 

front spar of the Centre Wing Box (CWB). 

This condition, if not detected and 

corrected, could lead to keel beam rupture 

which would affect the structural integrity of 

the area. 

Prompted by this potential unsafe 

condition, EASA issued AD 2006–0315 

[http://ad.easa.europa.eu/blob/easa_ad_

2006_0315.pdf/AD_2006-0315] (later revised 

to R1) to require repetitive special detailed 

inspections (SDI) [rotating probe inspection 

for cracking] on the horizontal flange of the 

keel beam in the area of first fastener hole aft 

of Frame (FR) 40 in order to maintain the 

structural integrity of the aeroplane. 

After that [EASA] AD was issued, EASA 

issued AD 2010–0024 [which corresponds to 

FAA AD 2011–24–05, Amendment 39–16869 

(76 FR 73496, November 29, 2011)], retaining 

the inspection requirements of EASA AD 

2006–0315R1 [http://ad.easa.europa.eu/blob/ 

easa_ad_2006_0315R1.pdf/AD_2006- 

0315R1], which was superseded, extending 

the applicability to aeroplanes with Airbus 

Mod 49202 embodied, and reducing the 

inspection thresholds and intervals. 

Since that [EASA] AD [2010–0024] was 

issued, a new fatigue and damage tolerance 

evaluation has been conducted by Airbus, 

which concluded that due to the aeroplane 

utilization, the current inspection threshold 

and intervals have to be modified. 

In addition, it was determined that the 

rototest inspection of fastener hole Nr 6, 

necessary to ensure that no crack was left 

unrepaired at the time of fastener hole cold 

working, was inadvertently not included in 


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1498 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations 

Revisions 01 and 02 of both Airbus Service 

Bulletin (SB) A330–57–3098 and A340–57– 

4106. 

Prompted by these findings, EASA issued 

AD 2014–0010 [http://ad.easa.europa.eu/

blob/easa_ad_2014-0010.pdf/AD_2014-0010], 

retaining the requirements of EASA AD 

2010–0024, which was superseded, and 

redefined the inspection thresholds and 

intervals [by reducing certain compliance 

times], and added a one-time ultrasonic 

inspection of fastener hold Nr 6 in the 

junction keel beam fitting at FR40 on both LH 

and RH side[s]. 

Following issuance of EASA AD 2014– 

0010, it was identified that there was a need 

for clarifications [of affected airplanes] 

* * *. 

The compliance times vary depending 

on airplane utilization and 

configuration. The earliest compliance 

time for the initial rotating probe 

inspections is the later of (1) before 

10,400 total flight cycles or 67,800 total 

flight hours, whichever occurs first; and 

(2) within 24 months or 14,590 flight 

cycles or 43,790 flight hours, whichever 

occurs first. The latest compliance time 

for the initial inspections is the later of 

(1) before 20,800 total flight cycles or 

67,900 total flight hours, whichever 

occurs first; and (2) within 24 months or 

21,180 flight cycles or 63,560 flight 

hours, whichever occurs first. The 

compliance times for the repetitive 

intervals range between 7,800 flight 

cycles or 50,900 flight hours and 10,700 

flight cycles or 35,200 flight hours. The 

compliance times for the one-time 

ultrasonic inspection are the latest of (1) 

21,000 flight cycles or 60,600 flight 

hours and within 2,400 flight cycles or 

24 months; or the latest of (2) 22,100 

flight cycles and 64,400 flight hours, or 

within 1,300 flight cycles or 24 months. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-0937- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 25249, May 4, 2015) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available 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 (80 FR 

25249, May 4, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 25249, 

May 4, 2015). 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. 

• Airbus Service Bulletin A330–57– 

3081, Revision 05, dated November 13, 

2012. 

• Airbus Service Bulletin A330–57– 

3090, Revision 01, dated June 15, 2011. 

• Airbus Service Bulletin A330–57– 

3098, dated August 30, 2007. 

• Airbus Service Bulletin A330–57– 

3098, Revision 02, June 15, 2011. 

• Airbus Service Bulletin A330–57– 

3098, Revision 03, dated September 24, 

2012. 

• Airbus Service Bulletin A330–57– 

3117, dated January 25, 2013. 

• Airbus Service Bulletin A340–57– 

4089, Revision 05, dated November 13, 

2012. 

• Airbus Service Bulletin A340–57– 

4098, Revision 01, dated June 15, 2011. 

• Airbus Service Bulletin A340–57– 

4106, dated August 30, 2007. 

• Airbus Service Bulletin A340–57– 

4106, Revision 02, dated June 15, 2011. 

• Airbus Service Bulletin A340–57– 

4106, Revision 03, dated September 24, 

2012. 

• Airbus Service Bulletin A340–57– 

4126, dated January 25, 2013. 

This service information describes 

procedures for inspections for cracking 

of the hole(s) of the horizontal flange of 

the keel beam, and contacting the 

manufacturer for repair instructions. 

Additionally, this service information 

describes procedures for a one-time 

ultrasonic inspection for cracking at 

fastener hole ‘‘Nr 6,’’ and provides 

optional terminating action for the 

repetitive inspections. 

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 35 

airplanes of U.S. registry. 

The actions that were required by AD 

2011–24–05, Amendment 39–16869 (76 

FR 73496, November 29, 2011), and 

retained in this AD take about 41 workhours per product, at an average labor 

rate of $85 per work hour. Required 

parts cost about $191 per product. Based 

on these figures, the estimated cost of 

the actions that were required by AD 

2011–24–05 is $3,676 per product. 

We also estimate that it takes about 23 

work-hours 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 on U.S. operators to be 

$68,425, or $1,955 per product. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this 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 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0937; 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 

AD, the regulatory evaluation, any 

comments received, and other 


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Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Rules and Regulations 1499 

information. The street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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 

■ 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 

removing Airworthiness Directive (AD) 

2011–24–05, Amendment 39–16869 (76 

FR 73496, November 29, 2011), and 

adding the following new AD: 

2015–25–10 Airbus: Amendment 39–18348. 

Docket No. FAA–2015–0937; Directorate 

Identifier 2014–NM–024–AD. 

(a) Effective Date 

This AD becomes effective February 17, 

2016. 

(b) Affected ADs 

This AD replaces AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011). 

(c) Applicability 

(1) This AD applies to the airplanes 

identified in paragraphs (c)(1)(i) and (c)(1)(ii) 

of this AD, certificated in any category, 

except as provided by paragraph (c)(2) of this 

AD. 

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

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

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

serial numbers, except those on which 

Airbus modification 55306 or 55792 has been 

embodied in production. 

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

–311, –312, and –313 airplanes, all serial 

numbers, except those on which Airbus 

modification 55306 or 55792 has been 

embodied in production. 

(2) This AD does not apply to Airbus 

Model A340–211, –212, –213, –311, –312, 

and –313 airplanes on which the repair 

specified in Airbus Repair Drawing 

R57115053, R57115051, or R57115047 

(installation of titanium doubler on both 

sides) has been accomplished. AD 2007–12– 

08, Amendment 39–15086 (72 FR 31171, 

June 6, 2007), applies to these airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of cracks 

on the keel beam fitting and the front spar 

of the center wing box. This AD was also 

prompted by a determination that the rototest 

inspection and applicable corrective actions 

of fastener hole ‘‘Nr 6’’ were inadvertently 

omitted from the requirements in AD 2011– 

24–05, Amendment 39–16869 (76 FR 73496, 

November 29, 2011). We are issuing this AD 

to detect and correct cracking of the fastener 

holes, which could result in rupture of the 

keel beam, and consequent reduced 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Non-Destructive Test (NDT) 

Inspection 

This paragraph restates the requirements of 

paragraph (n) of AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011), with new service 

information and revised credit for certain 

actions. At the applicable time in paragraph 

(g)(1) or (g)(2) of this AD, do an NDT 

inspection of the hole(s) of the horizontal 

flange of the keel beam located on frame (FR) 

40 datum on the right-hand (RH) and/or lefthand (LH) side of the fuselage, in accordance 

with the Accomplishment Instructions of the 

applicable service information specified in 

paragraph (g)(3), (g)(4), (g)(5), or (g)(6) of this 

AD. Accomplishing an inspection required 

by paragraph (j) of this AD terminates the 

inspections required by this paragraph. 

(1) For airplanes on which an inspection 

required by paragraph (h) of AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011), has not been done as of 

January 3, 2012 (the effective date of AD 

2011–24–05): At the applicable time 

specified in paragraph (g)(1)(i) or (g)(1)(ii) of 

this AD. 

(i) For all airplanes except those identified 

in paragraph (g)(1)(ii) of this AD: Within the 

‘‘Mandatory Threshold’’ (flight cycles or 

flight hours) specified in table 1 of paragraph 

1.E.(2) of Airbus Mandatory Service Bulletin 

A330–57–3081, including Appendix 01, 

Revision 04, dated May 31, 2011; or Airbus 

Mandatory Service Bulletin A340–57–4089, 

including Appendix 01, Revision 04, dated 

May 31, 2011; as applicable; or within 3 

months after January 3, 2012 (the effective 

date AD 2011–24–05, Amendment 39–16869 

(76 FR 73496, November 29, 2011)); 

whichever occurs later. The compliance 

times for configurations 02 through 06 

specified in the ‘‘Mandatory Threshold’’ 

column in table 1 of paragraph 1.E., 

‘‘Compliance,’’ are total flight cycles and 

total flight hours. 

(ii) For Model A330–201, –202, –203, –223, 

–243, –301, –321, –322, –323, –341, –342, 

and –343 airplanes, except those on which 

Airbus modification 49202 has been 

embodied in production, or Airbus Service 

Bulletin A330–57–3090 has been embodied 

in service; and Model A340–200 and –300 

series airplanes, except those on which 

Airbus modification 49202 has been 

embodied in production or Airbus Service 

Bulletin A340–57–4098 has been embodied 

in service, and except Model A340–211, 

–212, –213, –311, –312, and –313 airplanes 

on which the repair specified in Airbus 

Repair Drawing R57115053, R57115051, or 

R57115047 has been accomplished: At the 

earlier of the times specified in paragraphs 

(g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD. 

(A) Within the ‘‘Mandatory Threshold’’ 

(flight cycles or flight hours) specified in 

table 1 of paragraph 1.E.(2) of Airbus Service 

Bulletin A340–57–4089, including Appendix 

01, Revision 02, dated January 24, 2006; or 

Airbus Service Bulletin A330–57–3081, 

including Appendix 01, Revision 02, dated 

January 24, 2006; depending on the 

configuration of the aircraft model; or within 

3 months after September 13, 2007 (the 

effective date of AD 2007–16–02, 

Amendment 39–15141 (72 FR 44731, August 

9, 2007)), whichever occurs later. The 

compliance times for Model A330 post-mod. 

41652 and pre-mod. 44360, post-mod. 44360, 

and pre-mod. 49202 (as specified in Airbus 

Service Bulletin A330–57–3081, including 

Appendix 01, Revision 02, dated January 24, 

2006); and Model A340 post-mod. 41652, 

post-mod. 43500 and pre-mod. 44360, postmod. 44360 and pre-mod. 49202, and weight 

variant 027 (as specified in Airbus Service 

Bulletin A340–57–4089, including Appendix 

01, Revision 02, dated January 24, 2006); 

specified in the ‘‘Mandatory Threshold’’ 

column in table 1 of paragraph 1.E., 

‘‘Compliance,’’ are total flight cycles and 

total flight hours. 

(B) Within the ‘‘Mandatory Threshold’’ 

(flight cycles or flight hours) specified in 

table 1 of paragraph 1.E.(2) of Airbus 

Mandatory Service Bulletin A330–57–3081, 

including Appendix 01, Revision 04, dated 

May 31, 2011; or Airbus Mandatory Service 

Bulletin A340–57–4089, including Appendix 

01, Revision 04, dated May 31, 2011; as 

applicable; or within 3 months after January 

3, 2012 (the effective date of AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011)); whichever occurs later. 

The compliance times for configurations 02 

through 06 specified in the ‘‘Mandatory 

Threshold’’ column in table 1 of paragraph 

1.E., ‘‘Compliance,’’ are total flight cycles and 

total flight hours. 

(2) For airplanes on which an inspection 

required by paragraph (h) of AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011), has been done as of 

January 3, 2012 (the effective date of AD 

2011–24–05): At the earlier of the times 

specified in paragraphs (g)(2)(i) and (g)(2)(ii) 

of this AD. 

(i) Within the ‘‘Mandatory Intervals’’ given 

in table 1 of paragraph 1.E.(2) of Airbus 

Service Bulletin A340–57–4089, including 

Appendix 01, Revision 02, dated January 24, 

2006; or Airbus Service Bulletin A330–57– 

3081, including Appendix 01, Revision 02, 

dated January 24, 2006; as applicable. 

(ii) Within the applicable ‘‘Mandatory 

Interval’’ specified in table 1 of Paragraph 

1.E.(2) of Airbus Mandatory Service Bulletin 

A330–57–3081, including Appendix 01, 

Revision 04, dated May 31, 2011; or Airbus 

Mandatory Service Bulletin A340–57–4089, 

including Appendix 01, Revision 04, dated 

May 31, 2011; as applicable; or within 3 


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months after January 3, 2012 (the effective 

date of AD 2011–24–05, Amendment 39– 

16869 (76 FR 73496, November 29, 2011)); 

whichever occurs later. 

(3) Airbus Mandatory Service Bulletin 

A330–57–3081, including Appendix 01, 

Revision 04, dated May 31, 2011. 

(4) Airbus Service Bulletin A330–57–3081, 

Revision 05, dated November 13, 2012. 

(5) Airbus Mandatory Service Bulletin 

A340–57–4089, including Appendix 01, 

Revision 04, dated May 31, 2011. 

(6) Airbus Service Bulletin A340–57–4089, 

Revision 05, dated November 13, 2012. 

(h) Retained Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (p) of AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011). If no cracking is found 

during any inspection required by paragraph 

(g) of this AD, do the actions required by 

paragraphs (h)(1) and (h)(2) of this AD. 

(1) Before further flight: Install a new or 

oversized fastener, as applicable; seal the 

fastener; and do all other applicable actions; 

in accordance with the Accomplishment 

Instructions of the applicable service 

information specified in paragraph (g)(3), 

(g)(4), (g)(5), or (g)(6) of this AD. 

(2) Repeat the inspection required by 

paragraph (g) of this AD thereafter at 

intervals not to exceed the ‘‘Mandatory 

Intervals’’ specified in Paragraph 1.E.(2) of 

Airbus Mandatory Service Bulletin A330–57– 

3081, including Appendix 01, Revision 04, 

dated May 31, 2011; or Airbus Mandatory 

Service Bulletin A340–57–4089, including 

Appendix 01, Revision 04, dated May 31, 

2011; as applicable. 

(i) Retained Corrective Action and Optional 

Modification 

(1) This paragraph restates the 

requirements of paragraph (o) of AD 2011– 

24–05, Amendment 39–16869 (76 FR 73496, 

November 29, 2011), with revised method of 

compliance language. If any cracking is 

found during any inspection required by 

paragraph (g) of this AD, before further flight, 

repair 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). 

(2) This paragraph restates the 

requirements of paragraph (r) of AD 2011– 

24–05, Amendment 39–16869 (76 FR 73496, 

November 29, 2011), with new service 

information and revised method of 

compliance language. Modifying the fastener 

installation in the junction keel beam fitting 

at FR 40, as specified in paragraph (i)(2)(i), 

(i)(2)(ii), (i)(2)(iii), or (i)(2)(iv) of this AD, as 

applicable, terminates the requirements of 

paragraphs (g) and (h) of this AD; except, for 

airplanes on which a crack was detected at 

hole 5 before oversizing of the keel beam, in 

accordance with step 3.B.(1)(b)3 of the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3098, dated 

August 30, 2007; or Airbus Service Bulletin 

A340–57–4106, dated August 30, 2007; or in 

accordance with step 3.C.(2)(c) of the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3098, Revision 03, 

dated September 24, 2012, or Airbus Service 

Bulletin A340–57–4106, Revision 03, dated 

September 24, 2012; before further flight, 

repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. In case of any 

crack finding during any modification 

specified in this paragraph: Where the 

service information specifies to contact 

Airbus, before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. 

(i) Modification in accordance with Airbus 

Service Bulletin A330–57–3098, dated 

August 30, 2007, before January 3, 2012 (the 

effective date of AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011)). 

(ii) Modification in accordance with Airbus 

Service Bulletin A330–57–3098, Revision 03, 

dated September 24, 2012, before the 

effective date of this AD. 

(iii) Modification in accordance with 

Airbus Service Bulletin A340–57–4106, 

dated August 30, 2007, before January 3, 

2012 (the effective date of AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011)). 

(iv) Modification in accordance with 

Airbus Service Bulletin A340–57–4106, 

Revision 03, dated September 24, 2012, 

before the effective date of this AD. 

(j) New Repetitive Rotating Probe 

Inspections 

At the applicable times specified in 

paragraphs (j)(1) and (j)(2) of this AD: Do a 

rotating probe inspection for cracking of the 

fastener hole(s) of the horizontal flange of the 

keel beam located on FR 40 datum on the RH 

and LH side of the fuselage, as applicable to 

airplane type and depending on airplane 

configuration and utilization, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–57–3081, 

Revision 05, dated November 13, 2012; or 

Airbus Service Bulletin A340–57–4089, 

Revision 05, dated November 13, 2012; as 

applicable. Repeat the inspection thereafter 

at intervals not to exceed the ‘‘Mandatory 

Intervals’’ specified in Paragraph 1.E.(2) of 

the Accomplishment Timescale of Airbus 

Service Bulletin A330–57–3081, Revision 05, 

dated November 13, 2012; or Airbus Service 

Bulletin A340–57–4089, Revision 05, dated 

November 13, 2012; as applicable. 

Accomplishing an inspection required by 

this paragraph terminates the inspections 

required by paragraph (g) of this AD. 

(1) For airplanes on which the inspection 

required by paragraph (g) of this AD has not 

been done as of the effective date of this AD: 

Do the inspection before exceeding the 

applicable compliance times specified in the 

‘‘Mandatory Threshold’’ column of the tables 

in paragraph 1.E.(2) of the Accomplishment 

Timescale of Airbus Service Bulletin A330– 

57–3081, Revision 05, dated November 13, 

2012; or Airbus Service Bulletin A340–57– 

4089, Revision 05, dated November 13, 2012; 

as applicable; or within 12 months after the 

effective date of this AD; whichever occurs 

later. 

(2) For airplanes on which the inspection 

required by paragraph (g) of this AD has been 

done as of the effective date of this AD: Do 

the inspection within the applicable 

compliance times specified in the 

‘‘Mandatory Interval’’ column of the tables in 

paragraph 1.E.(2) of the Accomplishment 

Timescale of Airbus Service Bulletin A330– 

57–3081, Revision 05, dated November 13, 

2012; or Airbus Service Bulletin A340–57– 

4089, Revision 05, dated November 13, 2012; 

as applicable; or within 12 months after the 

effective date of this AD; whichever occurs 

later. 

(k) Credit for Previous Actions 

(1) This paragraph provides credit for the 

initial rotating probe inspection that is part 

of the inspections required by paragraphs (g) 

and (j)(1) of this AD, if those actions were 

performed before the effective date of this AD 

using the service information specified in 

paragraph (k)(1)(i) or (k)(1)(ii) of this AD. 

This service information was incorporated by 

reference in AD 2011–24–05, Amendment 

39–16869 (76 FR 73496, November 29, 2011). 

(i) Airbus A330/A340 200–300 Technical 

Disposition F57D03012810, Issue B, dated 

August 18, 2003. 

(ii) Airbus A330/A340 Technical 

Disposition 582.0651/2002, Issue A, dated 

October 17, 2002. 

(2) This paragraph restates the credit for 

the actions specified in paragraph (k) of AD 

2011–24–05, Amendment 39–16869 (76 FR 

73496, November 29, 2011), if those actions 

were performed before January 3, 2012 (the 

effective date of AD 2011–24–05), using the 

service information specified in paragraphs 

(k)(2)(i) through (k)(2)(viii) of this AD. 

(i) Airbus Service Bulletin A330–57–3081, 

dated October 30, 2003, which is not 

incorporated by reference in this AD. 

(ii) Airbus Service Bulletin A330–57–3081, 

Revision 01, dated May 18, 2004, which is 

not incorporated by reference in this AD. 

(iii) Airbus Service Bulletin A330–57– 

3081, Revision 02, including Appendix 01, 

dated January 24, 2006, which was 

incorporated by reference in AD 2007–12–08, 

Amendment 39–15086 (72 FR 31171, June 6, 

2007). 

(iv) Airbus Mandatory Service Bulletin 

A330–57–3081, Revision 03, dated July 31, 

2009, which is not incorporated by reference 

in this AD. 

(v) Airbus Service Bulletin A340–57–4089, 

dated October 30, 2003, which is not 

incorporated by reference in this AD. 

(vi) Airbus Service Bulletin A340–57– 

4089, Revision 01, dated March 2, 2004, 

which is not incorporated by reference in this 

AD. 

(vii) Airbus Service Bulletin A340–57– 

4089, Revision 02, including Appendix 01, 

dated January 24, 2006, which was 

incorporated by reference in AD 2007–12–08, 

Amendment 39–15086 (72 FR 31171, June 6, 

2007). 

(viii) Airbus Mandatory Service Bulletin 

A340–57–4089, Revision 03, dated July 31, 

2009. 

(l) New One-Time Ultrasonic Inspection 

For airplanes in Configuration 2, as defined 

in the applicable service information 


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identified in paragraph (l)(3), (l)(4), (l)(5), or 

(l)(6) of this AD, on which the modification 

has been done as of the effective date of this 

AD in accordance with the Accomplishment 

Instructions of the applicable service 

information identified in paragraph (l)(3), 

(l)(4), (l)(5), or (l)(6) of this AD; as applicable 

to airplane type; and on which fastener hole 

‘‘Nr 5’’ has been bushed before embodiment 

of Airbus Service Bulletin A330–57–3098 or 

Airbus Service Bulletin A340–57–4106, as 

applicable; or on which a crack has been 

found on fastener hole ‘‘Nr 5’’ during 

embodiment of Airbus Service Bulletin 

A330–57–3098 or Airbus Service Bulletin 

A340–57–4106, as applicable: At the 

applicable time specified in paragraph (l)(1) 

or (l)(2) of this AD, do a one-time ultrasonic 

inspection for cracking at fastener hole ‘‘Nr 

6’’ in the junction keel beam fitting at FR 40 

LH and RH sides, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3117, dated 

January 25, 2013; or Airbus Service Bulletin 

A340–57–4126, dated January 25, 2013; as 

applicable. 

(1) For Model A330–201, –202, –203, –223, 

–243, –301, –321, –322, –323, –341, –342, 

and –343 airplanes: At the later of the times 

specified in paragraphs (l)(1)(i) and (l)(1)(ii) 

of this AD. 

(i) At the applicable time specified in 

paragraph 1.E.(2), of the Accomplishment 

Timescale of Airbus Service Bulletin A330– 

57–3117, dated January 25, 2013. 

(ii) Within 2,400 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first. 

(2) For Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: At the later of the 

times specified in paragraphs (l)(2)(i) and 

(l)(2)(ii) of this AD. 

(i) At the applicable time specified in 

paragraph 1.E.(2) of the Accomplishment 

Timescale of Airbus Service Bulletin A340– 

57–4126, dated January 25, 2013. 

(ii) Within 1,300 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first. 

(3) Airbus Service Bulletin A330–57–3098, 

excluding Appendix 1, Revision 01, dated 

July 31, 2009. 

(4) Airbus Service Bulletin A330–57–3098, 

Revision 02, dated June 15, 2011. 

(5) Airbus Service Bulletin A340–57–4106, 

excluding Appendix 1, Revision 01, dated 

July 31, 2009. 

(6) Airbus Service Bulletin A340–57–4106, 

Revision 02, dated June 15, 2011. 

(m) Corrective Actions 

(1) If no cracking is found during any 

inspection required by paragraph (j) of this 

AD, before further flight: Install new or 

oversized fastener, as applicable; seal the 

fastener; and do all other applicable 

corrective actions; in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3081, Revision 05, 

dated November 13, 2012; or Airbus Service 

Bulletin A340–57–4089, Revision 05, dated 

November 13, 2012; as applicable. Thereafter, 

repeat the inspection required by paragraph 

(j) of this AD at intervals not to exceed the 

‘‘Mandatory Intervals’’ specified in Paragraph 

1.E.(2) of the Accomplishment Timescale of 

Airbus Service Bulletin A330–57–3081, 

Revision 05, dated November 13, 2012; or 

Airbus Service Bulletin A340–57–4089, 

Revision 05, dated November 13, 2012; as 

applicable. 

(2) If any crack is found during any 

inspection required by paragraph (j) or (l) of 

this AD; before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(n) Airplanes Excluded From Certain 

Requirements 

(1) For airplanes on which a rototest was 

done at fastener hole ‘‘Nr 6’’ before cold 

working of the fastener hole during 

accomplishment of the actions specified in 

the applicable service information identified 

in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or 

(n)(1)(iv) of this AD: The ultrasonic 

inspection specified in paragraph (l) of this 

AD is not required. 

(i) Airbus Service Bulletin A330–57–3098, 

excluding Appendix 1, Revision 01, dated 

July 31, 2009. 

(ii) Airbus Service Bulletin A330–57–3098, 

Revision 02, dated June 15, 2011. 

(iii) Airbus Service Bulletin A340–57– 

4106, excluding Appendix 1, Revision 01, 

dated June 31, 2009. 

(iv) Airbus Service Bulletin A340–57– 

4106, Revision 02, dated June 15, 2011. 

(2) For airplanes that have been modified 

as of the effective date of this AD in 

accordance with the Accomplishment 

Instructions of the applicable service 

information identified in paragraph (n)(1)(i), 

(n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD: 

No action is required by this paragraph, 

except as otherwise required by paragraph (l) 

of this AD and, provided that if any crack 

was found during any modification specified 

in this paragraph and the service information 

specified to contact Airbus, repair was done 

before further flight using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(o) Optional Terminating Actions 

(1) Modification of an airplane in 

accordance with the Accomplishment 

Instructions of the applicable service 

information identified in paragraph (o)(1)(i), 

(o)(1)(ii), (o)(1)(iii), (o)(1)(iv), (o)(1)(v), or 

(o)(1)(vi) of this AD; as applicable to airplane 

type and depending on airplane 

configuration; terminates the requirements of 

this AD, provided that in case of any crack 

finding during any modification specified in 

this paragraph, and the service information 

specifies to contact Airbus, repair is done 

before further flight, using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

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

DOA. If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(i) Airbus Service Bulletin A330–57–3090, 

dated March 27, 2006. 

(ii) Airbus Service Bulletin A330–57–3090, 

Revision 01, dated June 15, 2011. 

(iii) Airbus Service Bulletin A330–57– 

3098, Revision 03, dated September 24, 2012. 

(iv) Airbus Service Bulletin A340–57– 

4098, dated March 27, 2006. 

(v) Airbus Service Bulletin A340–57–4098, 

Revision 01, dated June 15, 2011. 

(vi) Airbus Service Bulletin A340–57– 

4106, Revision 03, dated September 24, 2012. 

(2) Accomplishment of the ultrasonic 

inspection required by paragraph (l) of this 

AD and all applicable corrective actions 

required by paragraph (m) of this AD 

terminate the requirements of this AD for 

those airplanes. 

(p) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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) AMOCs approved previously for AD 

2011–24–05, Amendment 39–16869 (76 FR 

73496, November 29, 2011), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(3) Contacting the Manufacturer: As of the 

effective date of this AD, 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 DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0010R1, dated 

May 5, 2014, 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– 

2015–0937–0002. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD is available at the addresses specified 

in paragraphs (r)(5) and (r)(6) of this AD. 

(r) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 


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(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. 

(3) The following service information was 

approved for IBR on February 17, 2016. 

(i) Airbus Service Bulletin A330–57–3081, 

Revision 05, dated November 13, 2012. 

(ii) Airbus Service Bulletin A330–57–3090, 

Revision 01, dated June 15, 2011. 

(iii) Airbus Service Bulletin A330–57– 

3098, dated August 30, 2007. 

(iv) Airbus Service Bulletin A330–57– 

3098, Revision 02, June 15, 2011. 

(v) Airbus Service Bulletin A330–57–3098, 

Revision 03, dated September 24, 2012. 

(vi) Airbus Service Bulletin A330–57– 

3117, dated January 25, 2013. 

(vii) Airbus Service Bulletin A340–57– 

4089, Revision 05, dated November 13, 2012. 

(viii) Airbus Service Bulletin A340–57– 

4098, Revision 01, dated June 15, 2011. 

(ix) Airbus Service Bulletin A340–57– 

4106, dated August 30, 2007. 

(x) Airbus Service Bulletin A340–57–4106, 

Revision 02, dated June 15, 2011. 

(xi) Airbus Service Bulletin A340–57– 

4106, Revision 03, dated September 24, 2012. 

(xii) Airbus Service Bulletin A340–57– 

4126, dated January 25, 2013. 

(4) The following service information was 

approved for IBR on January 3, 2012 (76 FR 

73496, November 29, 2011). 

(i) Airbus Mandatory Service Bulletin 

A330–57–3081, including Appendix 01, 

Revision 04, dated May 31, 2011. 

(ii) Airbus Service Bulletin A330–57–3098, 

Revision 01, excluding Appendix 1, dated 

July 31, 2009. 

(iii) Airbus Mandatory Service Bulletin 

A340–57–4089, including Appendix 01, 

Revision 04, dated May 31, 2011. 

(iv) Airbus Service Bulletin A340–57– 

4106, excluding Appendix 1, Revision 01, 

dated July 31, 2009. 

(5) The following service information was 

approved for IBR on September 13, 2007 (72 

FR 44731, August 9, 2007). 

(i) Airbus Service Bulletin A330–57–3081, 

Revision 02, including Appendix 01, dated 

January 24, 2006. 

(ii) Airbus Service Bulletin A340–57–4089, 

Revision 02, including Appendix 01, dated 

January 24, 2006. 

(6) 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. 

(7) 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. 

(7) 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/ibrlocations.html. 

Issued in Renton, Washington, on 

December 9, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–32256 Filed 1–12–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4213; Directorate 

Identifier 2015–CE–022–AD; Amendment 

39–18359; AD 2016–01–01] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Piper Aircraft, Inc. Model PA–46–500TP 

airplanes. This AD was prompted by a 

report of the wing upper skin joints 

being manufactured without sealant, 

which allows water to enter and stay in 

sealed, bonded stringers. This AD 

requires inspecting the upper wing 

surface for sealant; inspecting the wing 

stringers for water intrusion; inspecting 

for deformation and corrosion if 

evidence of water intrusion exists; and 

taking corrective actions as necessary. 

We are issuing this AD to correct the 

unsafe condition on these products. 

DATES: This AD is effective February 17, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 17, 2016. 

ADDRESSES: For service information 

identified in this AD, contact Piper 

Aircraft, Inc., Customer Service, 2926 

Piper Drive, Vero Beach, Florida 32960; 

telephone: (877) 879–0275; fax: none; 

email: customer.service@piper.com; 

Internet: www.piper.com. You may view 

this referenced service information at 

the FAA, Small Airplane Directorate, 

901 Locust, Kansas City, Missouri 

64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

locating Docket No. FAA–2015–4213. 

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–2015– 

4213; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone: 800–647– 

5527) is Document Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Gregory ‘‘Keith’’ Noles, Aerospace 

Engineer, FAA, Atlanta Aircraft 

Certification Office, 1701 Columbia 

Avenue, College Park, Georgia 30337; 

telephone: (404) 474–5551; fax: (404) 

474–5606; email: gregory.noles@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Piper Aircraft, Inc. 

Model PA–46–500TP airplanes. The 

NPRM published in the Federal 

Register on October 19, 2015 (80 FR 

63151). The NPRM was prompted by a 

report of wing upper skin joints on 

Piper Aircraft, Inc. Model PA–46–500TP 

airplanes being manufactured without 

sealant, which allows water to enter and 

stay in sealed, bonded stringers. The 

NPRM proposed to require inspecting 

the upper wing surface for sealant; 

inspecting the wing stringers for water 

intrusion; inspecting for deformation 

and corrosion if evidence of water 

intrusion exists; and taking corrective 

actions as necessary. We are issuing this 

AD to correct the unsafe condition on 

these products. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Piper Aircraft, Inc. 

Service Bulletin No. 1262B, dated April 

23, 2015. The service bulletin provides 

instructions for inspecting the upper 

wing surface for sealant and sealing or 

resealing (if necessary). This service 

bulletin also provides instructions for 

inspecting the wing stringers for water 

intrusion, and, if water intrusion was 

found as a result of the inspection, 

inspecting for corrosion or deformation. 

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 of 

this final rule. 


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