Federal Register / Vol. 79, No. 37 / Tuesday, February 25, 2014 / Proposed Rules 10431 

this AD, do inspections of the skin and bear 

straps and all applicable corrective actions 

using a method approved in accordance with 

the procedures specified in paragraph (m) of 

this AD. 

(i) Optional Terminating Actions 

(1) For Groups 1 and 2 airplanes identified 

in Boeing Alert Service Bulletin 737– 

53A1116, Revision 4, dated September 30, 

2013: Accomplishment of a repair before the 

effective date of this AD in the upper aft 

corner of the forward galley service doorway, 

in accordance with any service information 

specified in paragraphs (i)(1)(i) through 

(i)(1)(iv) of this AD, terminates the 

requirement for the repetitive inspection 

required by paragraph (g) of this AD for that 

repaired doorway corner only. 

(i) Boeing Service Bulletin 737–53–1116, 

dated July 21, 1988. 

(ii) Boeing Service Bulletin 737–53–1116, 

Revision 1, dated September 7, 1989. 

(iii) Boeing Service Bulletin 737–53–1116, 

Revision 2, dated September 30, 1993. 

(iv) Boeing Service Bulletin 737–53–1116, 

Revision 3, dated July 27, 1995. 

(2) For Group 2 airplanes identified in 

Boeing Alert Service Bulletin 737–53A1116, 

Revision 4, dated September 30, 2013, on 

which no repair or modification was done 

using any of the service information 

identified in paragraphs (i)(2)(i) through 

(i)(2)(iv) of this AD; and for Group 3 

airplanes identified in Boeing Alert Service 

Bulletin 737–53A1116, Revision 4, dated 

September 30, 2013: Repairing or modifying 

the upper aft corner of the forward galley 

service doorway, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1116, Revision 4, 

dated September 30, 2013, terminates the 

repetitive inspections required by paragraph 

(g) of this AD for that repaired or modified 

doorway corner only. 

(i) Boeing Service Bulletin 737–53–1116, 

dated July 21, 1988. 

(ii) Boeing Service Bulletin 737–53–1116, 

Revision 1, dated September 7, 1989. 

(iii) Boeing Service Bulletin 737–53–1116, 

Revision 2, dated September 30, 1993. 

(iv) Boeing Service Bulletin 737–53–1116, 

Revision 3, dated July 27, 1995. 

(3) For Groups 2 and 3 airplanes identified 

in Boeing Alert Service Bulletin 737– 

53A1116, Revision 4, dated September 30, 

2013: Repairing or modifying the lower 

forward or lower aft corner of the forward 

galley service doorway, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–53A1116, 

Revision 4, dated September 30, 2013, 

terminates the repetitive inspection required 

by paragraph (g) of this AD for that repaired 

or modified doorway corner only. 

(j) Exceptions to the Service Information 

(1) Where Boeing Alert Service Bulletin 

737–53A1116, Revision 4, dated September 

30, 2013, specifies a compliance time ‘‘after 

the Revision 4 date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time ‘‘after the effective 

date of this AD.’’ 

(2) Where Boeing Alert Service Bulletin 

737–53A1116, Revision 4, dated September 

30, 2013, specifies to contact Boeing for 

repair instructions: Before further flight, 

repair the cracking using a method approved 

in accordance with the procedures specified 

in paragraph (m) of this AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

inspections of the upper corners of the 

forward galley service doors specified in 

paragraph (g) of this AD, if those actions were 

performed before the effective date of this AD 

using any of the service information 

identified in paragraphs (k)(1) through (k)(4) 

of this AD (which are not incorporated by 

reference in this AD), provided that any 

preventative modification installed using this 

service information is inspected in 

accordance with paragraph (g) of this AD. 

(1) Boeing Service Bulletin 737–53–1116, 

dated July 21, 1988. 

(2) Boeing Service Bulletin 737–53–1116, 

Revision 1, dated September 7, 1989. 

(3) Boeing Service Bulletin 737–53–1116, 

Revision 2, dated September 30, 1993. 

(4) Boeing Service Bulletin 737–53–1116, 

Revision 3, dated July 27, 1995. 

(l) Post-Repair Inspections 

The post-repair inspections specified in 

Table 11 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1116, 

Revision 4, dated September 30, 2013, are not 

required by this AD. 

Note 1 to paragraph (l) of this AD: The 

post-repair inspections specified in Table 11 

of paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1116, 

Revision 4, dated September 30, 2013, may 

be used in support of compliance with 

section 121.1109(c)(2) or 129.109(b)(2) of the 

Federal Aviation Regulations (14 CFR 

121.1109(c)(2) or 14 CFR 129.109(b)(2)). 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-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 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6450; fax: (425) 917–6590; 

email: alan.pohl@faa.gov. 

(2) 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. 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. 

Issued in Renton, Washington, on February 

14, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04003 Filed 2–24–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0055; Directorate 

Identifier 2013–NM–167–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 A310–304, –322, –324, 

and –325 airplanes. This proposed AD 

was prompted by reports of insufficient 

clearance between the fuel quantity 

indicator (FQI) probes and the adjacent 

structure and metallic components in 

the wing fuel tanks. This proposed AD 

would require a one-time detailed visual 

inspection for sufficient clearance 

between FQI probes on both the lefthand side and right-hand side of the 

trim horizontal stabilizer and the 

adjacent structure and metallic 

components in the fuel tanks, and 

modification if necessary. We are 

proposing this AD to detect and correct 

insufficient clearance, which could lead 

to electrical arcing in a fuel tank during 

a lightning strike, which could result in 

ignition and consequent fire or 

explosion in the fuel tank. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
10432 Federal Register / Vol. 79, No. 37 / Tuesday, February 25, 2014 / Proposed Rules 

DATES: We must receive comments on 

this proposed AD by April 11, 2014. 

ADDRESSES: You may send comments 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 proposed AD, contact Airbus SAS, 

Airworthiness Office—EAW, 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. 

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– 

0055; 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–2125; 

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–2014–0055; Directorate Identifier 

2013–NM–167–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 

Community, has issued EASA 

Airworthiness Directive 2013–0188, 

dated August 19, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Airbus investigations on A300 aeroplanes 

revealed insufficient clearance between the 

Fuel Quantity Indicator (FQI) probes and 

adjacent structure or metallic components in 

the wing fuel tanks. A300–600 and A310 

aeroplanes are also affected as they are 

identical in design. 

This condition, if not detected and 

corrected, could lead to electric arcing in a 

fuel tank in case of lightning strike, which 

could result in ignition and consequent fire 

or explosion in the fuel tank. 

To address this potential unsafe condition, 

Airbus issued Service Bulletin (SB) A300– 

28–0080, SB A300–28–6065 and SB A310– 

28–2145 and DGAC France issued AD 2000– 

455–322 (http://ad.easa.europa.eu/ad/F2000-455-322) to cover A300 aeroplanes and 

AD 2002–170 (http://ad.easa.europa.eu/ad/

F-2002-170) to cover A300–600 and A310 

aeroplanes (both EASA ADs were later 

revised) [Both EASA ADs correspond to FAA 

AD 2004–05–05, Amendment 39–13499 (69 

FR 10319, dated March 5, 2004). 

Since those [EASA] ADs were issued, 

further analysis showed that they do not 

cover all potentially affected aeroplanes: 

A310 aeroplanes with optional Mod. no. 

12248 embodied were excluded from the 

applicability of DGAC France AD 2002– 

170(B) [http://ad.easa.europa.eu/ad/F-2002- 

170], but are potentially affected, and 

therefore addressed through this [EASA] AD. 

For the reasons described above, this 

[EASA] AD (http://ad.easa.europa.eu/ad/

2013-0188) requires a one-time [detailed 

visual] inspection of the affected aeroplanes 

for sufficient clearance between FQI probes 

[on both the left-hand (LH) side and righthand (RH) side of the trim horizontal 

stabilizer] and adjacent structure/metallic 

parts and, depending on findings, 

modification of the FQI probes. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2014–0055. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A310–28–2145, Revision 01, dated 

March 4, 2003. The actions described in 

this service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

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 the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 2 airplanes of U.S. registry. 

We also estimate that it would take 

about 8 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $1,360, or $680 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. We have 

no way of determining the number of 

products that may 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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 37 / Tuesday, February 25, 2014 / Proposed Rules 10433 

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–2014–0055; 

Directorate Identifier 2013–NM–167–AD. 

(a) Comments Due Date 

We must receive comments by April 11, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A310– 

304, –322, –324, and –325 airplanes, 

certificated in any category, on which Airbus 

modification number 12248 has been 

embodied. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by reports of 

insufficient clearance between the fuel 

quantity indicator (FQI) probes and the 

adjacent structure and metallic components 

in the wing fuel tanks. We are issuing this 

AD to detect and correct insufficient 

clearance, which could lead to electrical 

arcing in a fuel tank during a lightning strike, 

which could result in ignition and 

consequent fire or explosion in the fuel tank. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Modification 

Within 30 months after the effective date 

of this AD, do a one-time detailed visual 

inspection for clearance between the FQI 

probes located in the trimmable horizontal 

stabilizer tank and the adjacent structure and 

metallic components, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–28–2145, Revision 01, 

dated March 4, 2003. 

(1) If the clearance of an FQI probe is found 

to be 3.0 millimeters (mm) (0.118 inch) or 

more: No further action is required by 

paragraph (g) of this AD. 

(2) If the clearance of an FQI probe is found 

to be 2.5 mm (0.98 inch) or more, and less 

than 3.0 mm (0.118 inch): Before further 

flight, loosen the probe screws and move the 

probe up and down to get the required 

minimum gap of 3.0 mm (0.118 inch), in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310– 

28–2145, Revision 01, dated March 4, 2003. 

(3) If the clearance of an FQI probe is found 

to be less than 2.5 mm (0.118 inch): Before 

further flight, modify each affected FQI probe 

by installing new FQI probe supports, in 

accordance with Step 3.C., ‘‘Repair,’’ of the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–28–2145, Revision 01, 

dated March 4, 2003. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A310–28–2145, dated August 21, 

2001. 

(i) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–2125; 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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or by the Design 

Approval Holder with a State of Design 

Authority’s design organization approval). 

For a repair method to be approved, the 

repair approval must specifically refer to this 

AD. You are required to ensure the product 

is airworthy before it is returned to service. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0188, dated August 19, 2013, 

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 it in Docket No. FAA–2014– 

0055. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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. 

Issued in Renton, Washington, on February 

14, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04000 Filed 2–24–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0056; Directorate 

Identifier 2013–NM–160–AD] 

RIN 2120–AA64 

Airworthiness Directives; Saab AB, 

Saab Aerosystems 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 

Saab AB, Saab Aerosystems Model 

SAAB 2000 airplanes. This proposed 

AD was prompted by a report of rudder 


tkelley on DSK3SPTVN1PROD with PROPOSALS