1772 Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Proposed Rules 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702 and 44704. 

■ 2. Amend § 25.795 by redesignating 

paragraphs (d) and (e) as (e) and (f) 

respectively, and by adding a new 

paragraph (d) to read as follows: 

§ 25.795 Security considerations. 

* * * * * 

(d) Each chemical oxygen generator or 

its installation must be designed to be 

secure from deliberate manipulation by 

one of the following: 

(1) By providing effective resistance to 

tampering, 

(2) By providing an effective 

combination of resistance to tampering 

and active tamper-evident features, 

(3) By installation in a location or 

manner whereby any attempt to access 

the generator would be immediately 

obvious, or 

(4) By a combination of approaches 

specified in paragraphs (d)(1), (d)(2) and 

(d)(3) of this section that the 

Administrator finds provides a secure 

installation. 

* * * * * 

■ 3. Amend § 25.1450 by adding a new 

paragraph (b)(3) to read as follows: 

§ 25.1450 Chemical oxygen generators. 

* * * * * 

(b) * * * 

(3) Except as provided in SFAR 109, 

each chemical oxygen generator 

installation must meet the requirements 

of § 25.795(d). 

* * * * * 

Issued in Washington, DC, on January 3, 

2013. 

Dorenda D. Baker, 

Director, Aircraft Certification Service. 

[FR Doc. 2013–00238 Filed 1–8–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1316; Directorate 

Identifier 2012–NM–186–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to revise an 

existing airworthiness directive (AD) 

that applies to all The Boeing Company 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. The 

existing AD 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, various 

inspections for discrepancies at the aft 

pressure bulkhead, and related 

investigative and corrective actions if 

necessary. Since we issued that AD, we 

have determined that certain inspection 

and repair conditions must be clarified, 

as well as certain paragraph references 

related to the terminating action. This 

proposed AD would clarify certain 

actions specified in the existing AD. We 

are proposing this AD to detect and 

correct fatigue cracking, which could 

result in rapid decompression of the 

fuselage. 

DATES: We must receive comments on 

this proposed AD by February 25, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

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: 

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–2012–1316; Directorate Identifier 

2012–NM–186–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On August 31, 2012, we issued AD 

2012–18–13, Amendment 39–17190 (77 

FR 57990, September 19, 2012), for all 

The Boeing Company Model 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes. (AD 2012–18–13 

superseded AD 99–08–23, Amendment 

39–11132 (64 FR 19879, April 23, 

1999).) That AD 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, various 

inspections for discrepancies at the aft 

pressure bulkhead, and related 

investigative and corrective actions if 

necessary. That AD resulted from 

several reports of fatigue cracking at that 

location. We issued that AD to detect 

and correct such fatigue cracking, which 

could result in rapid decompression of 

the fuselage. 

Actions Since Existing AD (77 FR 

57990, September 19, 2012) Was Issued 

Since we issued AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012), we have 

determined that a certain inspection and 

repair required by paragraph (l) of AD 

2012–18–13 must be clarified. 


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Paragraph (l) of the existing AD 

specifies to inspect for ‘‘incorrectly 

drilled fasteners and elongated 

fasteners’’ (as well as for cracking and 

corrosion), and also that ‘‘if any crack, 

incorrectly drilled fastener, elongated 

fastener, or corrosion is found, before 

further flight, repair the web * * * .’’ 

However, the intent of paragraph (l) of 

AD 2012–18–13 with regard to this 

inspection is to inspect the fastener 

holes, not the fasteners. This also 

reflects the corresponding instructions 

specified in Boeing Alert Service 

Bulletin 737–53A1214, Revision 4, 

dated December 16, 2011 (which is the 

appropriate source of service 

information for accomplishing the 

actions required by paragraph (l) of AD 

2012–18–13). It is not possible to 

inspect ‘‘fasteners’’ using the procedures 

specified in Part III of the 

Accomplishment Instructions of that 

service bulletin. That is, the inspection 

procedures in that service bulletin apply 

to ‘‘fastener holes’’ and cannot be used 

to inspect ‘‘fasteners.’’ Therefore, we 

have revised paragraph (l) of this 

proposed AD to specify to inspect, in 

part, for ‘‘incorrectly drilled fastener 

holes’’ and ‘‘elongated fastener holes,’’ 

as well as to specify that ‘‘if any crack, 

incorrectly drilled fastener hole, 

elongated fastener hole, or corrosion is 

found, before further flight, repair 

* * *.’’ 

In addition, we also find it necessary 

to revise certain paragraph references 

related to the terminating action, as 

specified in paragraph (s) of AD 2012– 

18–13, Amendment 39–17190 (77 FR 

57990, September 19, 2012). Paragraph 

(s) of AD 2012–18–13 states that 

accomplishing the requirements of 

paragraphs (k) through (q) of that AD 

terminates the requirements of 

paragraphs (g) through (j) of that AD. 

However, we have determined that it is 

only necessary to accomplish the 

requirements of paragraph (k) of that AD 

in order to terminate the requirements 

of paragraphs (g) through (j) of that AD. 

We have revised paragraph (s) of this 

AD accordingly. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain all 

requirements of AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012). This proposed AD 

would clarify certain actions in 

paragraph (l) of this proposed AD, 

would revise certain paragraph 

references related to the terminating 

action in paragraph (s) of this proposed 

AD, and would add new paragraph 

(u)(5) to this proposed AD as a new 

provision of the alternative method of 

compliance (AMOC) paragraph to allow 

the continued use of AMOCs approved 

previously in accordance with AD 

2012–18–13. 

Costs of Compliance 

We estimate that this proposed AD 

affects 566 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

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

Low frequency eddy current (LFEC) inspection 

[retained action 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 

Detailed visual inspection [retained action 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 

(HFEC), 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 [retained actions from AD 

2012–18–13, Amendment 39–17190 (77 FR 

57990, September 19, 2012)].

Up to 60 work-hours × 

$85 per hour = 

$5,100 per inspection 

cycle.

$0 Up to $5,100 per inspection cycle.Up to $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 inspection 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 proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 


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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 

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 that the 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 AD: 

The Boeing Company: Docket No. FAA– 

2012–1316; Directorate Identifier 2012– 

NM–186–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by February 25, 2013. 

(b) Affected ADs 

This AD revises AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012). 

(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 (g) of AD 

2012–18–13, Amendment 39–17190 (77 FR 

57990, September 19, 2012). Perform either 

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 (h) of AD 2012– 

18–13, Amendment 39–17190 (77 FR 57990, 

September 19, 2012). 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 (i) of AD 

2012–18–13, Amendment 39–17190 (77 FR 

57990, September 19, 2012). 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 (j) of AD 2012– 

18–13, Amendment 39–17190 (77 FR 57990, 

September 19, 2012). 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) Retained Inspections of the Web at the 

‘‘Y’’ Chord Upper Bulkhead From S–15L to 

S–15R 

This paragraph restates the inspections of 

the web at the ‘‘Y’’ chord upper bulkhead 

from S–15L to S–15R required by paragraph 

(k) of AD 2012–18–13, Amendment 39–17190 

(77 FR 57990, September 19, 2012). 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 high 

frequency eddy current (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 


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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) Retained Inspections of the Web at the 

‘‘Y’’ Chord in the Lower Bulkhead From S– 

15L to S–15R With Revised Inspection and 

Repair Conditions 

This paragraph restates the inspections of 

the web at the ‘‘Y’’ chord in the lower 

bulkhead from S–15L to S–15R required by 

paragraph (l) of AD 2012–18–13, Amendment 

39–17190 (77 FR 57990, September 19, 2012), 

with revised inspection and repair 

conditions. 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 fastener holes, and 

elongated fastener holes, 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 hole, elongated fastener hole, 

or corrosion 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 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) Retained One-Time Inspection Under the 

Tear Strap 

This paragraph restates the one-time 

inspection under the tear strap required by 

paragraph (m) of AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012). 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) Retained Inspection for Oil-Canning 

This paragraph restates the inspection for 

oil-canning required by paragraph (n) of AD 

2012–18–13, Amendment 39–17190 (77 FR 

57990, September 19, 2012). 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. 

(o) Retained Inspection of the Dome Cap at 

the Center of the Bulkhead 

This paragraph restates the inspection of 

the dome cap at the center of the bulkhead 

required by paragraph (o) of AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012). 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) Retained Inspection of the Forward 

Flange of the ‘‘Z’’ Stiffeners at the Dome Cap 

This paragraph restates the inspection of 

the forward flange of the ‘‘Z’’ stiffeners at the 

dome cap required by paragraph (p) of AD 

2012–18–13, Amendment 39–17190 (77 FR 

57990, September 19, 2012). 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) Retained Inspection for Existing Repairs 

on the Bulkhead 

This paragraph restates the inspection for 

existing repairs on the bulkhead required by 

paragraph (q) of AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012). 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 

an HFEC inspection or an 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. 


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1776 Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Proposed Rules 

(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) Retained Exceptions to the Service 

Information 

This paragraph restates the exceptions to 

the service information required by 

paragraph (r) of AD 2012–18–13, Amendment 

39–17190 (77 FR 57990, September 19, 2012). 

(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 October 24, 2012 (the effective date 

of AD 2012–18–13, Amendment 39–17190 

(77 FR 57990, September 19, 2012)). 

(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 October 24, 

2012 (the effective date of AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012)). 

(s) Retained Terminating Action With 

Revised Paragraph Reference 

This paragraph restates the terminating 

action specified in paragraph (s) of AD 2012– 

18–13, Amendment 39–17190 (77 FR 57990, 

September 19, 2012), with a revised 

paragraph reference. Accomplishment of the 

requirements in paragraph (k) of this AD 

terminates the requirements of paragraphs (g) 

through (j) of this AD. 

(t) Credit for Previous Actions 

This paragraph restates the credit for 

previous actions specified by paragraph (t) of 

AD 2012–18–13, Amendment 39–17190 (77 

FR 57990, September 19, 2012). 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 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 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. 

(5) AMOCs approved previously in 

accordance with AD 2012–18–13, 

Amendment 39–17190 (77 FR 57990, 

September 19, 2012), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(v) 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, Washington 98057– 

3356; phone: (425) 917–6440; 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, 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. 

Issued in Renton, Washington, on January 

2, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–00186 Filed 1–8–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1217; Directorate 

Identifier 2012–NE–39–AD] 

RIN 2120–AA64 

Airworthiness Directives; International 

Aero Engines AG Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

International Aero Engines AG (IAE), 

V2525–D5 and V2528–D5 turbofan 

engines, with a certain number (No.) 4 

bearing internal scavenge tube and a 

certain No. 4 bearing external scavenge 

tube installed. This proposed AD was 

prompted by a report of an engine 

under-cowl fire and commanded inflight shutdown. This proposed AD 

would require replacement of certain 

part number (P/N) No. 4 bearing internal 

scavenge tubes, and alignment checks of 

certain P/N No. 4 bearing external 

scavenge tubes. We are proposing this 

AD to prevent engine fire and damage 

to the airplane. 


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