57990 Federal Register / Vol. 77, No. 182 / Wednesday, September 19, 2012 / Rules and Regulations 

pounds; turkeys and all other poultry— 

3 pounds. 

* * * * * 

Dated: September 13, 2012. 

David R. Shipman, 

Administrator, Agricultural Marketing 

Service. 

[FR Doc. 2012–23083 Filed 9–18–12; 8:45 am] 

BILLING CODE 3410–02–P 

NATIONAL CREDIT UNION 

ADMINISTRATION 

12 CFR Part 741 

RIN 3133–AD66 

Interest Rate Risk Policy and Program 

Correction 

In rule document 2012–02091, 

appearing on pages 55155–5167 in the 

issue of Thursday, February 2, 2012, 

make the following corrections: 

1. On page 5157, in the second 

column, in the first line, the text entry 

‘‘by asset size cohort at year-end 2010, 

as depicted in Table 1:’’ is deleted. 

2. On page 5164, in the second 

column, under the heading ‘‘Account 

Attributes’’ on the second line, 

‘‘P\principal’’ should read ‘‘Principal’’. 

[FR Doc. C1–2012–2091 Filed 9–18–12; 8:45 am] 

BILLING CODE 1505–01–D 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0645; Directorate 

Identifier 2011–NM–052–AD; Amendment 

39–17190; AD 2012–18–13] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all The Boeing Company Model 737– 

100, –200, –200C, –300, –400, and –500 

series airplanes. That AD currently 

requires repetitive inspections to detect 

cracking in the web of the aft pressure 

bulkhead at body station 1016 at the aft 

fastener row attachment to the ‘‘Y’’ 

chord, and corrective actions if 

necessary. This new AD adds various 

inspections for discrepancies at the aft 

pressure bulkhead, and related 

investigative and corrective actions if 

necessary. This AD was prompted by 

several reports of fatigue cracking at that 

location. We are issuing this AD to 

detect and correct such fatigue cracking, 

which could result in rapid 

decompression of the fuselage. 

DATES: This AD is effective October 24, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 24, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of May 10, 1999 (64 FR 

19879, April 23, 1999). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may review copies of the 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations.

gov; 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 (phone: 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: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

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

alan.pohl@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 99–08–23, 

Amendment 39–11132 (64 FR 19879, 

April 23, 1999). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

June 28, 2012 (77 FR 38547). That 

NPRM proposed to continue to require 

repetitive inspections to detect cracking 

in the web of the aft pressure bulkhead 

at body station 1016 at the aft fastener 

row attachment to the ‘‘Y’’ chord, and 

corrective actions if necessary. That 

NPRM also proposed to require adding 

various inspections for discrepancies at 

the aft pressure bulkhead, and related 

investigative and corrective actions if 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Boeing supports the NPRM (77 FR 

38547, June 28, 2012). Aviation Partners 

Boeing stated that it has reviewed the 

NPRM and has determined that the 

installation of winglets per 

supplemental type certificate 

ST01219SE does not affect the NPRM. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 566 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Low frequency eddy current (LFEC) inspection [retained actions from AD 

99-08–23, Amendment 39–11132 (64 

FR 19879, April 23, 1999)].

8 work-hours × $85 per hour = $680 ..... $0 $680 ....................... $384,880. 


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Federal Register / Vol. 77, No. 182 / Wednesday, September 19, 2012 / Rules and Regulations 57991 

ESTIMATED COSTS—Continued 

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Detailed visual inspection [retained actions from AD 99-08-23, Amendment 

39–11132 (64 FR 19879, April 23, 

1999)].

2 work-hours × $85 per hour = $170 ..... 0 170 ......................... 96,220. 

Detailed, high frequency eddy current 

inspection, and LFEC inspections of 

the web at the ‘‘Y’’ chord of the bulkhead, the web located under the 

outer circumferential tear strap, the 

‘‘Z’’ stiffeners at the dome cap, and 

existing repairs [new action].

Up to 60 work-hours × $85 per hour = 

$5,100 per inspection cycle.

0 5,100 per inspection cycle.2,886,600 per inspection cycle. 

We estimate the following costs to do 

any necessary on-condition inspections 

that would be required based on the 

results of the initial inspection. We have 

no way of determining the number of 

aircraft that might need these 

inspections: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Detailed and HFEC inspections for oil-canning ........... 1 work-hour × $85 per hour = $85 ............................... $0 $85 

LFEC or HFEC inspections for cracking ...................... 2 work-hours × $85 per hour = $170 ........................... 0 170 

We have received no definitive data 

that would enable us to provide cost 

estimates for the crack repairs 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 have 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 

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 

removing airworthiness directive (AD) 

99–08–23, Amendment 39–11132 (64 

FR 19879, April 23, 1999), and adding 

the following new AD: 

2012–18–13 The Boeing Company: 

Amendment 39–17190; Docket No. 

FAA–2012–0645; Directorate Identifier 

2011–NM–052–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 24, 2012. 

(b) Affected ADs 

This AD supersedes AD 99–08–23, 

Amendment 39–11132 (64 FR 19879, April 

23, 1999). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes; 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by several reports 

of fatigue cracks in the aft pressure bulkhead. 

We are issuing this AD to detect and correct 

such fatigue cracking, which could result in 

rapid decompression of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Initial Inspection 

This paragraph restates the initial 

inspection required by paragraph (a) of AD 

99–08–23, Amendment 39–11132 (64 FR 

19879, April 23, 1999). Perform either 


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57992 Federal Register / Vol. 77, No. 182 / Wednesday, September 19, 2012 / Rules and Regulations 

inspection specified by paragraph (g)(1) or 

(g)(2) of this AD at the time specified in 

paragraph (h) of this AD. 

(1) Perform a low frequency eddy current 

(LFEC) inspection from the aft side of the aft 

pressure bulkhead to detect discrepancies 

(including cracking, misdrilled fastener 

holes, and corrosion) of the web of the upper 

section of the aft pressure bulkhead at body 

station 1016 at the aft fastener row 

attachment to the ‘‘Y’’ chord, from stringer 15 

left (S–15L) to stringer 15 right (S–15R), in 

accordance with Boeing 737 Nondestructive 

Test Manual D6–37239, Part 6, Section 53– 

10–54, dated December 5, 1998. 

(2) Perform a detailed visual inspection of 

the aft fastener row attachment to the ‘‘Y’’ 

chord from the forward side of the aft 

pressure bulkhead to detect discrepancies 

(including cracking, misdrilled fastener 

holes, and corrosion) of the entire web of the 

aft pressure bulkhead at body station 1016. 

(h) Retained Compliance Times 

This paragraph restates the compliance 

times specified in paragraph (b) of AD 99– 

08–23, Amendment 39–11132 (64 FR 19879, 

April 23, 1999). Perform the inspection 

required by paragraph (g) of this AD at the 

time specified in paragraph (h)(1), (h)(2), or 

(h)(3) of this AD, as applicable. 

(1) For airplanes that have accumulated 

40,000 or more total flight cycles as of May 

10, 1999 (the effective date of AD 99–08–23, 

Amendment 39–11132 (64 FR 19879, April 

23, 1999)): Inspect within 375 flight cycles or 

60 days after May 10, 1999 (the effective date 

of AD 99–08–23), whichever occurs later. 

(2) For airplanes that have accumulated 

25,000 or more total flight cycles and fewer 

than 40,000 total flight cycles as of May 10, 

1999 (the effective date of AD 99–08–23, 

Amendment 39–11132 (64 FR 19879, April 

23, 1999)): Inspect within 750 flight cycles or 

90 days after May 10, 1999 (the effective date 

of AD 99–08–23), whichever occurs later. 

(3) For airplanes that have accumulated 

fewer than 25,000 total flight cycles as of 

May 10, 1999 (the effective date of AD 99– 

08–23, Amendment 39–11132 (64 FR 19879, 

April 23, 1999)): Inspect prior to the 

accumulation of 25,750 total flight cycles. 

(i) Retained Repetitive Inspections 

This paragraph restates the repetitive 

inspections required by paragraph (c) of AD 

99–08–23, Amendment 39–11132 (64 FR 

19879, April 23, 1999). Within 1,200 flight 

cycles after performing the initial inspection 

required by paragraph (g) of this AD, and 

thereafter at intervals not to exceed 1,200 

flight cycles: Perform either inspection 

specified by paragraph (g)(1) or (g)(2) of this 

AD. 

(j) Retained Corrective Actions 

This paragraph restates the corrective 

actions required by paragraph (d) of AD 99– 

08–23, Amendment 39–11132 (64 FR 19879, 

April 23, 1999). If any discrepancy is 

detected during any inspection required by 

paragraph (g), (h), or (i) of this AD: Prior to 

further flight, accomplish the actions 

specified by paragraphs (j)(1) and (j)(3) of this 

AD, and paragraph (j)(2) of this AD, if 

applicable. 

(1) Perform a high frequency eddy current 

inspection from the forward side of the 

bulkhead to detect cracking of the web at the 

‘‘Y’’ chord attachment, around the entire 

periphery of the ‘‘Y’’ chord, in accordance 

with Boeing 737 Nondestructive Test Manual 

D6–37239, Part 6, Section 51–00–00, Figure 

23, dated November 5, 1995. 

(2) If the most recent inspection performed 

in accordance with paragraph (g) of this AD 

was not a detailed visual inspection: 

Accomplish the actions specified by 

paragraph (g)(2) of this AD. If the inspection 

was a detailed visual inspection, it is not 

necessary to repeat that inspection prior to 

further flight. 

(3) Repair any discrepancy such as 

cracking or corrosion or misdrilled fastener 

holes using a method approved in 

accordance with the procedures specified in 

paragraph (u) of this AD. 

(k) New Requirements: Inspections of the 

Web at the ‘‘Y’’ Chord Upper Bulkhead From 

S–15L to S–15R 

At the later of the times specified in 

paragraphs (k)(1) and (k)(2) of this AD: Do 

detailed and LFEC inspections of the aft side 

of the bulkhead web, or do detailed and 

HFEC inspections from the forward side of 

the bulkhead, and do all applicable related 

investigative and corrective actions; in 

accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1214, Revision 4, 

dated December 16, 2011, except as required 

by paragraphs (r)(1) and (r)(3) of this AD. 

Inspect for cracks, incorrectly drilled fastener 

holes, and elongated fastener holes. Do all 

applicable related investigative and 

corrective actions before further flight. 

Repeat the inspections at the applicable 

times specified in table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011. 

(1) Prior to the accumulation of 25,000 

total flight cycles. 

(2) Except as required by paragraphs (r)(2) 

and (r)(4) of this AD, at the later of the times 

specified in the ‘‘Compliance Time’’ column 

in table 1 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 737– 

53A1214, Revision 4, dated December 16, 

2011. 

(l) New Requirements: Inspections of the 

Web at the ‘‘Y’’ Chord in the Lower 

Bulkhead From S–15L to S–15R 

Except as required by paragraphs (r)(2) and 

(r)(5) of this AD, at the applicable time 

specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011: Do detailed and eddy 

current inspections of the web from the 

forward or aft side of the bulkhead for cracks, 

incorrectly drilled fasteners, and elongated 

fasteners, in accordance with Part III of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1214, Revision 4, 

dated December 16, 2011, except as required 

by paragraphs (r)(1) and (r)(3) of this AD. If 

any crack, incorrectly drilled fastener, 

elongated fastener, or corrosion is found, 

before further flight, repair the web using a 

method approved in accordance with the 

procedures specified in paragraph (u) of this 

AD. Repeat the inspections at the applicable 

times specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011. 

(m) New Requirements: One-Time Inspection 

Under the Tear Strap 

Except as required by paragraphs (r)(2) and 

(r)(5) of this AD, at the applicable time 

specified in table 3 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011: Do a one-time LFEC 

inspection for cracks on the aft side of the 

bulkhead of the web located under the outer 

circumferential tear strap, or do a one-time 

HFEC inspection for cracks from the forward 

side of the bulkhead of the web located under 

the outer circumferential tear strap, in 

accordance with Part II of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1214, Revision 4, 

dated December 16, 2011, except as required 

by paragraph (r)(1) of this AD. If any cracking 

is found, before further flight, repair the 

bulkhead using a method approved in 

accordance with the procedures specified in 

paragraph (u) of this AD. 

(n) New Requirements: Inspection for OilCanning 

Except as required by paragraph (r)(2) of 

this AD, at the applicable time specified in 

table 4 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011: Do a 

detailed inspection from the aft side of the 

bulkhead for oil-canning and do all 

applicable related investigative and 

corrective actions, in accordance with Part II 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011, except 

as required by paragraph (r)(1) of this AD. Do 

all related investigative and corrective 

actions before further flight. Thereafter, 

repeat the inspection at the applicable times 

specified in table 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011. For oil-cans found 

within the limits specified in Part II of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1214, Revision 4, 

dated December 16, 2011: In lieu of installing 

the repair before further flight, at the 

applicable times specified in table 4 of 

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

Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011, do 

initial and repetitive detailed and HFEC 

inspections for cracks of the oil-canning and 

install the repair, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1214, Revision 4, 

dated December 16, 2011. If any crack is 

found, before further flight, repair the 

cracking using a method approved in 

accordance with the procedures specified in 

paragraph (u) of this AD. Installing the repair 

terminates the repetitive inspections for 

cracks. 


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Federal Register / Vol. 77, No. 182 / Wednesday, September 19, 2012 / Rules and Regulations 57993 

(o) New Requirements: Inspection of the 

Dome Cap at the Center of the Bulkhead 

Except as required by paragraphs (r)(2) and 

(r)(5) of this AD, at the applicable time 

specified in table 5 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011: Do an eddy current 

inspection to detect any cracking of the dome 

cap at the center of the bulkhead, and do all 

applicable corrective actions, in accordance 

with Part IV of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1214, Revision 4, dated December 

16, 2011. Do all corrective actions before 

further flight. Repeat the inspection at the 

times specified in table 5 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011. 

(p) New Requirements: Inspection of the 

Forward Flange of the ‘‘Z’’ Stiffeners at the 

Dome Cap 

Except as required by paragraphs (r)(2) and 

(r)(5) of this AD, at the applicable time 

specified in table 6 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011: Do an HFEC inspection 

to detect any cracking of the ‘‘Z’’ stiffener 

flanges at the dome cap in the center of the 

bulkhead, in accordance with Part V of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1214, Revision 4, 

dated December 16, 2011, except as required 

by paragraph (r)(1) of this AD. If any crack 

is found, before further flight, repair the 

flanges using a method approved in 

accordance with the procedures specified in 

paragraph (u) of this AD. Repeat the 

inspection at the applicable times specified 

in table 6 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 737– 

53A1214, Revision 4, dated December 16, 

2011. 

(q) New Requirements: Inspection for 

Existing Repairs on the Bulkhead 

Except as required by paragraph (r)(2) of 

this AD, at the applicable time specified in 

table 7 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011: Do a 

detailed inspection of the bulkhead web and 

stiffeners for existing repairs, in accordance 

with Part VI of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1214, Revision 4, dated December 

16, 2011, except as required by paragraph 

(r)(1) of this AD. 

(1) If any repair identified in the 

‘‘Condition’’ column of table 8 of paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011, is found and the 

‘‘Reference’’ column refers to Appendix A, B, 

C, or D of that service bulletin: At the 

applicable times specified in table 8 of 

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

Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011, except 

as required by paragraph (r)(2) of this AD, do 

a HFEC inspection or a LFEC inspection of 

the web for cracking, in accordance with 

Appendix A, B, C, or D, as applicable, of 

Boeing Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011. If any 

cracking is found, before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (u) of 

this AD. Repeat the inspections, thereafter, at 

the applicable intervals specified in table 8 

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

Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011. 

(2) If any repair identified in the 

‘‘Condition’’ column of table 8 of paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011, is found and the 

‘‘Reference’’ column refers to Appendix E of 

that service bulletin: At the applicable times 

specified in table 8 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011, except as required by 

paragraph (r)(2) of this AD, remove the repair 

and replace with a new repair, in accordance 

with Appendix E of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011. 

(3) If any non-SRM (structural repair 

manual) repair is found and the repair does 

not have FAA-approved damage tolerance 

inspections, except as required by paragraph 

(r)(2) of this AD, at the applicable time 

specified in table 7 of Paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011: Contact the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

Aircraft Certification Office, for damage 

tolerance inspections. Do those damage 

tolerance inspections at the times given using 

a method approved in accordance with the 

procedures specified in paragraph (u) of this 

AD. 

(r) Exceptions to the Service Information 

(1) Where Boeing Alert Service Bulletin 

737–53A1214, Revision 4, dated December 

16, 2011, specifies to contact Boeing for 

repair instructions: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (u) of this AD. 

(2) Where Boeing Alert Service Bulletin 

737–53A1214, Revision 4, dated December 

16, 2011, specifies a compliance time ‘‘after 

the date of Revision 1 to this service 

bulletin,’’ ‘‘from the date of Revision 3 of this 

service bulletin,’’ ‘‘after the date of Revision 

3 to this service bulletin,’’ or ‘‘of the effective 

date of AD 99–08–23,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(3) Access and restoration procedures 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1214, Revision 4, dated December 

16, 2011, are not required by this AD. 

Operators may do those procedures following 

their maintenance practices. 

(4) Where table 1 of paragraph 1.E., 

‘‘Compliance’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011, specifies a compliance 

time relative to actions done ‘‘in accordance 

with paragraph (a)(2) of AD 99–08–23,’’ this 

AD requires compliance within the specified 

compliance time relative to actions specified 

in paragraph (g)(2) of this AD. 

(5) Where the Condition columns in tables 

2, 3, 5, and 6 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, dated 

December 16, 2011, refer to total flight cycles, 

this AD applies to the airplanes with the 

specified total flight cycles as of the effective 

date of this AD. 

(s) Terminating Action 

Accomplishment of the requirements of 

paragraphs (k) through (q) of this AD 

terminates the requirements of paragraphs (g) 

through (j) of this AD. 

(t) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (k) through (s) 

of this AD, if the actions were performed 

before the effective date of this AD using the 

service bulletins specified in paragraphs 

(t)(1) through (t)(4) of this AD. 

(1) Boeing Alert Service Bulletin 737– 

53A1214, dated June 17, 1999. 

(2) Boeing Alert Service Bulletin 737– 

53A1214, Revision 1, dated June 22, 2000. 

(3) Boeing Alert Service Bulletin 737– 

53A1214, Revision 2, dated May 24, 2001. 

(4) Boeing Alert Service Bulletin 737– 

53A1214, Revision 3, dated January 19, 2011. 

(u) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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 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. 

(4) AMOCs approved previously in 

accordance with AD 99–08–23, Amendment 

39–11132 (64 FR 19879, April 23, 1999), are 

approved as AMOCs for the corresponding 

provisions of this AD. 

(v) Related Information 

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, Washington 98057– 

3356; phone: (425) 917–6440; fax: (425) 917– 

6590; email: alan.pohl@faa.gov. 


srobinson on DSK4SPTVN1PROD with RULES
57994 Federal Register / Vol. 77, No. 182 / Wednesday, September 19, 2012 / Rules and Regulations 

(w) 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. 

(3) The following service information was 

approved for IBR on October 24, 2012. 

(i) Boeing Alert Service Bulletin 737– 

53A1214, Revision 4, dated December 16, 

2011. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on May 10, 1999 (64 FR 

19879, April 23, 1999). 

(i) Boeing 737 Nondestructive Test Manual 

D6–37239, Part 6, Section 53–10–54, dated 

December 5, 1998. 

(ii) Boeing 737 Nondestructive Test 

Manual D6–37239, Part 6, Section 51–00–00, 

Figure 23, dated November 5, 1995. 

(5) For The Boeing Company service 

information identified in this AD, contact 

Boeing Commercial Airplanes, Attention: 

Data & Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124–2207; 

telephone 206–544–5000, extension 1; fax 

206–766–5680; Internet https://www.

myboeingfleet.com. 

(6) You may review copies of the 

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. 

(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/ibr-locations.html. 

Issued in Renton, Washington, on August 

31, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–22334 Filed 9–18–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0644; Directorate 

Identifier 2012–NM–011–AD; Amendment 

39–17193; AD 2012–18–16] 

RIN 2120–AA64 

Airworthiness Directives; The Cessna 

Aircraft Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Cessna Aircraft Company Model 

750 airplanes. This AD was prompted 

by reports of direct current (DC) 

generator overvoltage events. This AD 

requires replacing the auxiliary power 

unit (APU) generator control unit (GCU). 

We are issuing this AD to prevent DC 

generator overvoltage events, which 

could result in smoke in the cockpit and 

loss of avionics and electrical systems. 

DATES: This AD is effective October 24, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 24, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Cessna 

Aircraft Co., P.O. Box 7706, Wichita, 

Kansas 67277; telephone 316–517–6215; 

fax 316–517–5802; email 

citationpubs@cessna.textron.com; 

Internet https:// 

www.cessnasupport.com/newlogin.html. 

You may review copies of the 

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; 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 (phone: 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: 

Christine Abraham, Aerospace Engineer, 

Electrical Systems and Avionics Branch, 

ACE–119W, FAA, Wichita Aircraft 

Certification Office, 1801 Airport Road, 

Room 100, Mid-Continent Airport, 

Wichita, Kansas 67209; telephone: 316– 

946–4165; fax: 316–946–4107; email: 

christine.abraham@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on June 25, 2012 (77 FR 37827). 

That NPRM proposed to require 

replacing the auxiliary power unit 

(APU) generator control unit (GCU). 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 37827, June 25, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 58 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Replacement ....................................... 2 work-hours × $85 per hour = $170 ......................... $2,400 $2,570 $149,060 

According to the manufacturer, all of 

the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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 


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