This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

19467 

Vol. 81, No. 65 

Tuesday, April 5, 2016 

1 80 FR 21153 (Apr. 17, 2015). 

2 12 CFR 1026.58(g)(1). 

3 12 CFR 1026.58(c)(1). 

4http://www.consumerfinance.gov/credit-cards/

agreements/. 5 12 CFR 1026.58(d), (e), (g)(2). 

BUREAU OF CONSUMER FINANCIAL 

PROTECTION 

12 CFR Part 1026 

Submission of Credit Card Agreements 

Under the Truth in Lending Act 

(Regulation Z) 

AGENCY: Bureau of Consumer Financial 

Protection. 

ACTION: Notice of expiration of 

suspension. 

SUMMARY: The Truth in Lending Act 

(TILA) and Regulation Z require credit 

card issuers to submit their currentlyoffered credit card agreements to the 

Bureau of Consumer Financial 

Protection (Bureau), to be posted on the 

Bureau’s Web site. In April 2015, the 

Bureau suspended that submission 

obligation for a period of one year. That 

suspension has expired, and the next 

submission is due on the first business 

day on or after April 30, 2016 (i.e., May 

2, 2016). Credit card issuers should visit 

the Bureau’s Web site for instructions 

on submitting credit card agreements. 

DATES: Credit card issuers are required 

to submit to the Bureau the agreements 

they offered to the public as of March 

31, 2016, on or before May 2, 2016. 

FOR FURTHER INFORMATION CONTACT: 

Thomas L. Devlin, Counsel, or Kristine 

M. Andreassen, Senior Counsel, Office 

of Regulations, Consumer Financial 

Protection Bureau, 1700 G Street NW., 

Washington, DC 20552, at 202–435– 

7700. 

SUPPLEMENTARY INFORMATION: In April 

2015, the Bureau amended Regulation Z 

(12 CFR part 1026), which implements 

TILA, and the official interpretation to 

that regulation, to temporarily suspend 

card issuers’ obligations to submit credit 

card agreements to the Bureau for a 

period of one year i.e., the four quarterly 

submissions due to the Bureau by the 

first business day on or after April 30, 

2015; July 31, 2015; October 31, 2015; 

and January 31, 2016, respectively.1

The suspension began with the 

submission that would have been due 

on the first business day on or after 

April 30, 2015, and ended with the 

submission that would have been due 

on the first business day on or after 

January 31, 2016. Accordingly, card 

issuers must resume submitting 

agreements to the Bureau with the 

submission due on the first business day 

on or after April 30, 2016 (i.e., May 2, 

2016), covering credit card agreements 

that were offered to the public as of 

March 31, 2016.2 Regulation Z 

§ 1026.58(g) and comment 58(g)–2 

describe which agreements must be 

submitted to the Bureau as part of the 

submission due on May 2, 2016. 

Regulation Z provides that card 

issuers shall submit their currentlyoffered agreements ‘‘in the form and 

manner specified by the Bureau.’’ 3

Updated submission instructions are 

available through the Bureau’s Web 

site.4 Card issuers’ obligations to post 

currently-offered credit card agreements 

on their publicly available Web sites, 

and to make agreements for open 

accounts available to cardholders, were 

not affected by the suspension.5

Dated: March 28, 2016. 

Richard Cordray, 

Director, Bureau of Consumer Financial 

Protection. 

[FR Doc. 2016–07815 Filed 4–4–16; 8:45 am] 

BILLING CODE 4810–AM–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1047; Directorate 

Identifier 2014–NM–157–AD; Amendment 

39–18449; AD 2016–07–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This AD was 

prompted by a report that, during the 

assembly process, several gaps between 

the two parts of the girt bar fittings for 

the aft passenger doors were found to 

exceed tolerances. This AD requires an 

inspection of the gap between the two 

parts of the girt bar fittings on left-hand 

(LH) and right-hand (RH) aft passenger 

doors, and corrective actions if 

necessary. We are issuing this AD to 

detect and correct incorrect gaps 

between the girt bar fittings. Detachment 

of a girt bar could lead to the separation 

of the slide or slide-raft from the 

fuselage, making the emergency exit 

inoperative, which could impede an 

emergency evacuation. 

DATES: This AD becomes effective May 

10, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 10, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus, Airworthiness Office—EIAS, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone +33 5 

61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@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–2014– 

1047. 

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–2014– 

1047; 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 street address for 

the Docket Office (telephone 800–647– 

5527) is Docket Management Facility, 


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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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

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 Airbus Model A318, 

A319, A320, and A321 series airplanes. 

The NPRM published in the Federal 

Register on January 23, 2015 (80 FR 

3533) (‘‘the NPRM’’). The NPRM was 

prompted by a report that, during the 

assembly process, several gaps between 

the two parts of the girt bar fittings for 

the aft passenger doors were found to 

exceed tolerances. The NPRM proposed 

to require an inspection of the gap 

between the two parts of the girt bar 

fittings on LH and RH aft passenger 

doors, and corrective actions if 

necessary. We are issuing this AD to 

detect and correct incorrect gaps 

between the girt bar fittings. Detachment 

of a girt bar could lead to the separation 

of the slide or slide-raft from the 

fuselage, making the emergency exit 

inoperative, which could impede an 

emergency evacuation. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Reference Later Revision of 

Service Information 

United Airlines (UAL) proposed to 

update the reference to the service 

information to Airbus Service Bulletin 

A320–53–1289, Revision 01, dated 

August 29, 2014. UAL also suggested 

that the service information update 

would also update the effectivity for the 

applicable inspection. 

We agree to reference the latest 

service information, Airbus Service 

Bulletin A320–53–1289, Revision 01, 

dated August 29, 2014, which updates 

the effectivity, and have revised 

paragraph (g) of this AD accordingly. 

We have also added a new paragraph (i) 

to this AD to provide credit for actions 

done using Airbus Service Bulletin 

A320–53–1289, dated May 28, 2014, 

and have redesignated subsequent 

paragraphs accordingly. 

Request To Clarify the Tolerances for 

the Gap Size 

UAL requested clarification on the 

inspection task’s initial gap requirement 

tolerance and the required gap tolerance 

for trimmed latches. UAL stated that it 

seems the initial inspection in Task 

531289–832–601/602–001 of Airbus 

Service Bulletin A320–53–1289, 

Revision 01, dated August 29, 2014, 

specifies that a gap equal to or less than 

4 millimeters (mm) (0.158 inch) is 

acceptable without the need for further 

action, but other tasks for post-trimming 

and post-latch-replacement inspections 

specify replacement if the gap is less 

than 1 mm (0.0394 inch). UAL noted 

that those inspection tasks reference a 

figure in Airbus Service Bulletin A320– 

53–1289, Revision 01, dated August 29, 

2014, which specifies the gap should be 

between 1 mm (0.0394 inch) and 4 mm 

(0.158 inch). UAL also stated that the 

trimming action in Task 531289–831– 

601–001 of Airbus Service Bulletin 

A320–53–1289, Revision 01, dated 

August 29, 2014, specifies trimming the 

latch again if the gap is still greater than 

4 mm (0.158 inch), which seems to 

conflict with a figure that gives one trim 

dimension without any tolerance. UAL 

further stated that it should be clearer 

that the latch should be trimmed as 

many times as required with a 

maximum trim dimension of 0.5 mm 

(0.0197 inch) until the required gap 

tolerance is achieved. 

We agree to provide clarification. 

Figure A–SBCAA of Airbus Service 

Bulletin A320–53–1289, Revision 01, 

dated August 29, 2014, specifies 0.5 mm 

(0.0197 inch) as the limit of the edge 

margin, which must not be exceeded 

while trimming the latch part during the 

gap adjustment. We find that Airbus 

Service Bulletin A320–53–1289, 

Revision 01, dated August 29, 2014, is 

clear on the initial gap tolerance, which 

specifies corrective actions if the gap is 

initially greater than 4 mm (0.158 inch). 

The corrective actions include trimming 

and determining the gap after trimming. 

If the gap is less than 1 mm (0.0394 

inch) or greater than 4 mm (0.158 inch) 

after trimming, Airbus Service Bulletin 

A320–53–1289, Revision 01, dated 

August 29, 2014, specifies additional 

corrective actions. No change has been 

made to this final rule in this regard. 

Request To Address Issue of Obsolete 

Part Numbers 

UAL stated that the NPRM and the 

referenced service information (Airbus 

Service Bulletins A320–53–1289, dated 

May 28, 2014, and Revision 01, dated 

August 29, 2014) do not identify part 

number D531125020000 as obsolete, 

which is identified in the illustrated 

parts catalog (IPC) as an acceptable part. 

UAL pointed out that the referenced 

service information introduces new part 

numbers D5348027920–200/400 as part 

of a corrective action, but does not 

specify the new part numbers as a part 

of an action to require new or revised 

latch or girt bar assembly parts. UAL 

asserts that, without a revised IPC or 

specific steps in the service information, 

there is a risk that the old part number 

could be used in the future, and lead to 

an incorrect gap after accomplishing the 

inspection required by this AD. 

We agree to clarify the issue. This AD 

refers to Airbus Service Bulletin A320– 

53–1289, Revision 01, dated August 29, 

2014, as the appropriate source of 

service information for accomplishing 

the actions required by this AD. We 

have determined the information 

specified in Airbus Service Bulletin 

A320–53–1289, Revision 01, dated 

August 29, 2014, is adequate. In 

addition, the requirements of an AD 

take precedence over any specifications 

in an IPC, which is not an FAAapproved document. We recommend 

that operators work with the 

manufacturer to ensure there are no 

discrepancies in the IPC. It is the 

responsibility of operators to apply 

necessary controls to maintain the 

airplane in accordance with the 

required configuration of an AD. No 

change has been made to this final rule 

in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–53–1289, Revision 01, dated 

August 29, 2014. The service 

information describes procedures for a 

detailed inspection of the gap in the girt 

bar fittings of the aft passenger doors, 

LH and RH sides, and corrective actions. 


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Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Rules and Regulations 19469 

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 838 

airplanes of U.S. registry. 

We also estimate that it will take 

about 3 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 $213,690, or $255 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 4 work-hours and require parts 

costing $435, for a cost of $775 per 

product. We have no way of 

determining the number of aircraft that 

might need these actions. 

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. 

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 adding 

the following new airworthiness 

directive (AD): 

2016–07–04 Airbus: Amendment 39–18449. 

Docket No. FAA–2014–1047; Directorate 

Identifier 2014–NM–157–AD. 

(a) Effective Date 

This AD becomes effective May 10, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) through (c)(4) of this AD, 

except those on which Airbus Modification 

154966 has been embodied during 

production. 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–211, –212, –214, –231, 

–232, and –233 airplanes. 

(4) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report that, 

during the assembly process, several gaps 

between the two parts of the girt bar fittings 

for the aft passenger doors were found to 

exceed tolerances. We are issuing this AD to 

detect and correct incorrect gaps between the 

girt bar fittings. Detachment of a girt bar 

could lead to the separation of the slide or 

slide-raft from the fuselage, making the 

emergency exit inoperative, which could 

impede an emergency evacuation. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Corrective Action 

Except as provided by paragraph (h) of this 

AD, within 36 months after the effective date 

of this AD, do a detailed inspection of the 

gap in the girt bar fittings of the aft passenger 

doors, left-hand (LH) and right-hand (RH) 

sides, and do all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1289, Revision 01, 

dated August 29, 2014. Do all applicable 

corrective actions before further flight. 

(h) Exception 

For any airplane that has been modified to 

a configuration where one or both LH and RH 

aft passenger doors are permanently 

inoperative or deactivated: If any aft 

passenger door is reactivated, after 

reactivation but before further flight, do the 

detailed inspection of the reactivated aft 

passenger door(s) and all applicable 

corrective actions, as required by paragraph 

(g) of this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–53–1289, dated May 28, 2014, 

which is not incorporated by reference in this 

AD. 

(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, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; 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) Required for Compliance (RC): 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 


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19470 Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Rules and Regulations 

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. 

(3) 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 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2014–0178, dated July 25, 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–2014–1047. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (l)(3) and (l)(4) of this AD. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–53–1289, 

Revision 01, dated August 29, 2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

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

(4) 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. 

(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 March 

20, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–07028 Filed 4–4–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–5036; Directorate 

Identifier 2015–NM–180–AD; Amendment 

39–18453; AD 2016–07–08] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for a 

certain The Boeing Company Model 

DC–9–83 (MD–83) airplane. This AD 

requires installing fuel level float and 

pressure switch in-line fuses, and doing 

applicable wiring changes, on the left, 

right, and center wing forward spars, 

forward auxiliary fuel tank, and aft 

auxiliary fuel tank. This AD was 

prompted by fuel system reviews 

conducted by the manufacturer. We are 

issuing this AD to prevent the potential 

of ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

DATES: This AD is effective April 20, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 20, 2016. 

We must receive comments on this 

AD by May 20, 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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this final rule, 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, Washington. 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– 

5036. 

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– 

5036; 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 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: 

Samuel Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 

562–627–5262; fax: 562–627–5210; 

email: samuel.lee@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 (66 FR 

23086, May 7, 2001) requires certain 

type design (i.e., type certificate (TC) 

and supplemental type certificate (STC)) 


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