This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

65 

Vol. 79, No. 1 

Thursday, January 2, 2014 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0425; Directorate 

Identifier 2012–NM–224–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain The Boeing Company Model 

747 airplanes. The NPRM proposed to 

require repetitive inspections for 

cracking in the bulkhead splice fitting, 

frame supports, forward and aft inner 

chords, and floor support; an inspection 

for cracking in the bulkhead upper web, 

doubler, and bulkhead lower web; and 

corrective actions if necessary; for 

certain airplanes, inspections for 

cracking in the repaired area of the 

bulkhead, and corrective actions if 

necessary; for certain airplanes, support 

frame modification and support frame 

inspections, and related investigative 

and corrective actions, if necessary; for 

certain airplanes, repetitive support 

frame post-modification inspections and 

inspections for cracking in the hinge 

support, and related investigative and 

corrective actions if necessary; for 

certain airplanes, a one-time inspection 

of the frame web and upper shear deck 

(floor support) chord aft side for 

fasteners; and a one-time inspection of 

the upper forward inner chord, frame 

support fitting and splice fitting, for the 

installation of certain fasteners; and 

related investigative and corrective 

actions if necessary; for certain 

airplanes, a one-time inspection of the 

upper forward inner chord, frame 

support fitting and splice fitting for the 

installation of certain fasteners; a onetime inspection for any repair installed 

on the left and right side of the aft inner 

chord, and related investigative and 

corrective actions, if necessary; for 

certain airplanes, a one-time inspection 

of the support frame outer chords for 

cracking, and repair if necessary; and 

repetitive support frame post-repair 

inspections, and corrective actions, if 

necessary. The NPRM was prompted by 

reports of cracking in the forward and 

aft inner chord of the body station (BS) 

2598 bulkhead near the upper corners of 

the cutout for the horizontal stabilizer 

rear spar, and cracking in the bulkhead 

upper and lower web panels near the 

inner chord to shear deck connection. 

This action revises the NPRM by adding 

an optional terminating action for 

certain inspections and expanding the 

inspection area for certain surface and 

open-hole HFEC inspections. We are 

proposing this supplemental NPRM 

(SNPRM) to detect and correct fatigue 

cracking of the BS 2598 bulkhead 

structure, which could adversely affect 

the structural integrity of the bulkhead 

and the horizontal stabilizer support 

structure and result in loss of 

controllability of the airplane. Since 

these actions impose an additional 

burden over that proposed in the NPRM, 

we are reopening the comment period to 

allow the public the chance to comment 

on these proposed changes. 

DATES: We must receive comments on 

this SNPRM by February 18, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this 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, 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 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: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 

425–917–6590; email: 

nathan.p.weigand@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–2013–0425; Directorate Identifier 

2012–NM–224–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 

We issued an NPRM to amend 14 CFR 

part 39 to include an AD that would 

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66 Federal Register / Vol. 79, No. 1 / Thursday, January 2, 2014 / Proposed Rules 

apply to certain The Boeing Company 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747–400D, 747– 

400F, 747SR, and 747SP series 

airplanes, certificated in any category. 

The NPRM published in the Federal 

Register on May 28, 2013 (78 FR 31867). 

The NPRM proposed to require 

repetitive inspections for cracking in the 

bulkhead splice fitting, frame supports, 

forward and aft inner chords, and floor 

support; doing an inspection for 

cracking in the bulkhead upper web, 

doubler, and bulkhead lower web; and 

corrective actions if necessary; for 

certain airplanes, inspections for 

cracking in the repaired area of the 

bulkhead, and corrective actions if 

necessary; for certain airplanes, support 

frame modification and support frame 

inspections, and related investigative 

and corrective actions, if necessary; for 

certain airplanes, repetitive support 

frame post-modification inspections and 

inspections for cracking in the hinge 

support, and related investigative and 

corrective actions if necessary; for 

certain airplanes, a one-time inspection 

of the frame web and upper shear deck 

(floor support) chord aft side for 

fasteners; and a one-time inspection of 

the upper forward inner chord, frame 

support fitting and splice fitting, for the 

installation of certain fasteners; and 

related investigative and corrective 

actions if necessary; for certain 

airplanes, a one-time inspection of the 

upper forward inner chord, frame 

support fitting and splice fitting for the 

installation of certain fasteners; a onetime inspection for any repair installed 

on the left and right side of the aft inner 

chord, and related investigative and 

corrective actions, if necessary; for 

certain airplanes, a one-time inspection 

of the support frame outer chord for 

cracking, and repair if necessary; and 

repetitive support frame post-repair 

inspections, and corrective actions, if 

necessary. 

Actions Since Previous NPRM (78 FR 

31867, May 28, 2013) Was Issued 

Since we issued the NPRM (78 FR 

31867, May 28, 2013), we have received 

Boeing Alert Service Bulletin 747– 

53A2427, Revision 7, dated July 19, 

2013, which extends the open-hole 

HFEC inspection for cracking to include 

more fastener holes common to the 

upper and lower splice fittings on both 

sides of the bulkhead, plus some 

additional fastener holes adjacent to the 

lower splice fitting. Boeing Alert Service 

Bulletin 747–53A2427, Revision 7, 

dated July 19, 2013, also extends the 

surface HFEC inspection for cracking to 

include the fillet radius area of the 

upper splice fitting. Boeing Alert 

Service Bulletin 747–53A2427, Revision 

7, dated July 19, 2013, clarifies 

compliance times for the initial surface 

HFEC inspection of the upper web for 

airplanes modified or repaired before 

the upper web inspection was added. 

Boeing Alert Service Bulletin 747– 

53A2427, Revision 7, dated July 19, 

2013, also adds an optional terminating 

modification for certain inspections. 

Comments 

We gave the public the opportunity to 

comment on the NPRM (78 FR 31867, 

May 28, 2013). The following presents 

the comments received on the NPRM 

(78 FR 31867, May 28, 2013) and the 

FAA’s response to each comment. 

Request To Replace the NPRM (78 FR 

31867, May 28, 2013) 

Atlas Air, Inc. requested that the 

NPRM (78 FR 31867, May 28, 2013) be 

replaced with four separate ADs. The 

commenter stated that having a separate 

AD for Boeing Alert Service Bulletin 

747–53A2427, Revision 7, dated July 19, 

2013; Boeing Service Bulletin 747– 

53A2449, Revision 2, dated March 14, 

2002; Boeing Alert Service Bulletin 

747–53A2467, Revision 1, dated April 

28, 2005; and Boeing Service Bulletin 

747–53A2473, Revision 4, dated 

December 1, 2011; would simplify the 

requirements and future supersedures. 

The commenter also stated that separate 

ADs will ease the burden on the 

operators. 

We disagree with replacing the NPRM 

(78 FR 31867, May 28, 2013). Increasing 

the number of ADs to four does not 

necessarily ease the operator burden. 

We find that delaying this action to 

resubmit as a separate AD, would be 

inappropriate in light of the urgency of 

the identified unsafe condition. No 

changes have been made to this SNPRM 

in this regard. 

Request for Alternative Method of 

Compliance (AMOC) Approval for 

Previously Approved AMOCs 

Atlas Air, Inc. requested that AMOCs 

approved for paragraphs (i), (j), (m), (n), 

(o), (p), (q), (r), (s), (t), (u), and (v), of AD 

2010–14–07 (75 FR 38001, July 1, 2010), 

be approved as AMOCs to the 

corresponding actions of the NPRM (78 

FR 31867, May 28, 2013). 

We agree with the request. Although 

the actions in some of the paragraphs 

referenced above carry over to 

paragraphs (g), (h), (i), (j), (k), and (l) of 

this SNPRM, AD 2010–14–07 (75 FR 

38001, July 1, 2010) was superseded and 

added new inspections and 

requirements, for which previously 

approved AMOCs would not provide 

coverage. We have added new 

paragraph (q)(4) to this SNPRM stating 

that previously approved AMOCs for 

AD 2010–14–07 are approved for the 

corresponding actions in this SNPRM. 

All actions specified in paragraphs (g), 

(h), (i), (j), (k), and (l) of this SNPRM 

that are not identified in the AMOC 

must still be done. 

Request Authorization of Modification 

in Boeing Service Bulletin 747–53A2837 

as an AMOC to Requirements of 

Paragraphs (j), (k), and (l) of the NPRM 

(78 FR 31867, May 28, 2013) 

Atlas Air, Inc. requested that the 

NPRM (78 FR 31867, May 28, 2013) be 

revised to authorize the modification in 

Boeing Service Bulletin 747–53A2837 as 

an AMOC to the requirements of 

paragraphs (j), (k), and (l) of the NPRM. 

We agree with the request. Boeing 

Service Bulletin 747–53A2837, dated 

July 13, 2012, was approved as an 

AMOC to AD 2010–14–07 (75 FR 38001, 

July 1, 2010). Accomplishing the 

modification of the bulkhead at BS 

2598, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2837, dated 

July 13, 2012, terminates the 

requirements of paragraphs (g), (h), (i), 

(j), (k), and (l) of this AD. We have 

added new paragraph (n) to this SNPRM 

to provide this optional terminating 

modification. 

Request for Clarification of Language in 

Paragraph (g) of the NPRM (78 FR 

31867, May 28, 2013) 

Boeing requested that we delete the 

phrase, ‘‘and doubler,’’ and add the 

word, ‘‘assembly’’ to bulkhead upper 

web and bulkhead lower web in 

paragraph (g) of the NPRM (78 FR 

31867, May 28, 2013). Boeing stated that 

the language in Boeing Alert Service 

Bulletin 747–53A2427, Revision 6, 

dated July 14, 2011, was in error and 

this requested change clarifies the 

NPRM to match the intent of this service 

bulletin. 

We agree to clarify the language and 

have made the requested changes to 

paragraph (g) of this SNPRM 

accordingly. 

Request for Clarification of Language in 

Paragraph (m)(5) and (m)(6) of the 

NPRM (78 FR 31867, May 28, 2013) 

Boeing requested that we add the 

phrase ‘‘bonded web’’ to the word 

‘‘doubler’’ in paragraphs (m)(5) and 

(m)(6) of the NPRM (78 FR 31867, May 

28, 2013). Boeing stated that the 

language in Boeing Alert Service 

Bulletin 747–53A2427, Revision 6, 

dated July 14, 2011, was in error and 

this requested change clarifies the 

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Federal Register / Vol. 79, No. 1 / Thursday, January 2, 2014 / Proposed Rules 67 

NPRM to match the intent of this service 

bulletin. Boeing also requested that we 

add the phrase ‘‘if present’’ to paragraph 

(m)(6) of the NPRM. 

We agree to clarify the language and 

have made the requested changes to 

paragraphs (m)(5) and (m)(6) of this 

SNPRM accordingly. We have also 

added the phrase ‘‘if present’’ to 

paragraph (m)(6) of this SNPRM. 

Request To Correct Compliance Time 

Boeing requested that we correct the 

compliance time specified in paragraph 

(m)(2) of the NPRM (78 FR 31867, May 

28, 2013) to be from the effective date 

of AD 2010–14–07, Amendment 39– 

16352 (75 FR 38001, July 1, 2010). 

Boeing Alert Service Bulletin 747– 

53A2427, Revision 6, dated July 14, 

2011, was not mandated by AD 2006– 

05–06, Amendment 39–14503 (71 FR 

12125, March 9, 2006). 

We agree with the request and have 

made the change to paragraph (m)(2) of 

this SNPRM accordingly. 

Other Changes to SNPRM 

We have updated paragraphs (c), (g), 

(h), (i), (m), and (o) of this SNPRM to 

refer to Boeing Alert Service Bulletin 

747–53A2427, Revision 7, dated July 19, 

2013. We have also added the area of 

the upper and lower web panels to the 

open hole and surface HFEC inspections 

specified in paragraph (g) of this 

SNPRM. We have clarified the affected 

airplanes for paragraph (g) of this 

SNPRM by qualifying the airplanes to 

those on which an interim modification 

or aft inner chord repair has not been 

done, as specified in Boeing Alert 

Service Bulletin 747–53A2427. We have 

also provided credit for Boeing Alert 

Service Bulletin 747–53A2427, Revision 

6, dated July 14, 2011, provided that the 

additional actions added in Boeing Alert 

Service Bulletin 747–53A2427, Revision 

7, dated July 19, 2013, are done within 

the applicable compliance times 

specified in paragraphs (g), (h), and (i) 

of this SNPRM. 

FAA’s Determination 

We are proposing this SNPRM 

because we evaluated all the relevant 

information and determined the unsafe 

condition described previously is likely 

to exist or develop in other products of 

these same type designs. Certain 

changes described above expand the 

scope of the NPRM (78 FR 31867, May 

28, 2013). As a result, we have 

determined that it is necessary to reopen 

the comment period to provide 

additional opportunity for the public to 

comment on this SNPRM. 

Proposed Requirements of the SNPRM 

This SNPRM would require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 184 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 

Inspection .................................. 49 work-hours × $85 per hour 

= $4,165 per inspection 

cycle.

$0 $4,165 per inspection cycle ..... $766,360 per inspection 

cycle. 

Support frame modification ....... 315 work-hours × $85 per hour 

= $26,775.

$0 $26,775 .................................... Up to $4,926,600. 

Support frame upper corner fastener inspection.16 work-hours × $85 per hour 

= $1,360.

$0 $1,360 ...................................... Up to $250,240. 

Support frame post-modification 

inspection.

200 work hours × $85 per hour 

= $17,000.

$0 $17,000 .................................... $3,128,000. 

We estimate the following costs to do 

any necessary interim modification that 

would be required based on the results 

of the proposed inspection. We have no 

way of determining the number of 

aircraft that might need this interim 

modification: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Interim modification ...................................................... 4 work-hours × $85 per hour = $340 ........................... $0 $340 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the corrective actions 

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. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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, 

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68 Federal Register / Vol. 79, No. 1 / Thursday, January 2, 2014 / Proposed Rules 

(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): 

The Boeing Company: Docket No. FAA– 

2013–0425; Directorate Identifier 2012– 

NM–224–AD. 

(a) Comments Due Date 

We must receive comments by February 

18, 2014. 

(b) Affected ADs 

This AD affects AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, 747SR, and 

747SP series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 747–53A2427, Revision 7, 

dated July 19, 2013. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking in the forward and aft inner chord 

of the body station (BS) 2598 bulkhead near 

the upper corners of the cutout for the 

horizontal stabilizer rear spar, and cracking 

in the bulkhead upper and lower web panels 

near the inner chord to shear deck 

connection. We are issuing this AD to detect 

and correct fatigue cracking of the BS 2598 

bulkhead structure, which could adversely 

affect the structural integrity of the bulkhead 

and the horizontal stabilizer support 

structure and result in loss of controllability 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections of the Bulkhead (Support 

Frame) 

For airplanes on which the bulkhead 

(support frame) modification specified in 

Boeing Service Bulletin 747–53A2473 or 

747–53A2837 has not been accomplished, 

and on which an interim modification or aft 

inner chord repair has not been done as 

specified in Boeing Alert Service Bulletin 

747–53A2427: At the applicable times 

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

Boeing Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013, except as 

provided by paragraph (m)(1), (m)(2), or 

(m)(3) of this AD, as applicable, do an openhole and surface high frequency eddy current 

(HFEC) inspection for cracking in the 

bulkhead (support frame), which includes 

the bulkhead splice fitting, frame supports, 

forward and aft inner chords, floor supports, 

and upper and lower web panels; do a 

surface HFEC inspection for cracking in the 

bulkhead upper web assembly; do an openhole and surface HFEC inspection for 

cracking in the bulkhead lower web 

assembly; and do all applicable corrective 

actions; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2427, Revision 7, 

dated July 19, 2013, except as required by 

paragraphs (m)(4), (m)(5) and (m)(6) of this 

AD, and except as provided by paragraph (h) 

of this AD. Do all applicable corrective 

actions before further flight. Repeat the 

applicable inspections, thereafter, at the 

applicable times in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2427, Revision 7, dated July 

19, 2013. Doing the modification required by 

paragraph (j) of this AD terminates the 

repetitive inspections required by this 

paragraph. 

(h) Interim Modification 

For airplanes in groups 1 and 2, as 

identified in Boeing Alert Service Bulletin 

747–53A2427, Revision 7, dated July 19, 

2013, on which no cracking was found 

during any inspection required by paragraph 

(g) of this AD: At the applicable times 

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

Boeing Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013, except as 

provided by paragraph (m)(2) of this AD, do 

the interim modification, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013. Doing the 

interim modification terminates the 

repetitive inspections requirement of 

paragraph (g) of this AD in the area of the 

modification only. The repetitive inspections 

of the bulkhead lower web, as specified in 

paragraph (g) of this AD, must be done. If the 

aft inner chord repair or upper web repair 

specified in Boeing Alert Service Bulletin 

747–53A2427, Revision 7, dated July 19, 

2013, has been accomplished, an interim 

modification on the side of the airplane that 

has the repair is not required by this 

paragraph. 

(i) Post-Repair Inspection or Post-Interim 

Modification Inspection 

For airplanes on which an interim 

modification, or aft inner chord repair, or 

upper web repair has been done as specified 

in paragraph (g) or (h) of this AD: At the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2427, Revision 7, dated July 

19, 2013, except as specified in paragraph 

(m)(1), (m)(2), or (m)(3) of this AD, as 

applicable, do the actions specified in 

paragraph (i)(1) and (i)(2) of this AD, and all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013, except as 

required by paragraph (m)(4) of this AD. Do 

all applicable corrective actions before 

further flight. Repeat the inspections 

thereafter at the applicable intervals specified 

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

Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013. Doing the 

modification required by paragraph (j) of this 

AD terminates the repetitive inspections 

required by this paragraph. 

(1) Do forward side surface HFEC 

inspections for cracking of the bulkhead 

forward inner chord, splice fitting, and frame 

support. 

(2) Do surface and open-hole HFEC 

inspections for cracking in the repaired and 

modified areas of the bulkhead, as 

applicable. 

(j) Bulkhead (Support Frame) Modification 

and Inspections 

For airplanes on which the bulkhead 

(support frame) modification specified in 

Boeing Service Bulletin 747–53A2473, dated 

March 24, 2005; Revision 1, dated February 

20, 2007; Revision 2, dated August 28, 2009; 

Revision 3, dated July 14, 2011; or Revision 

4, dated December 1, 2011; has not been done 

as of the effective date of this AD: At the 

applicable time in tables 2 and 3 of paragraph 

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

Bulletin 747–53A2473, Revision 4, dated 

December 1, 2011, do the bulkhead (support 

frame) modification and inspections and all 

applicable related investigative and 

corrective actions; in accordance with steps 

3.B.3., 3.B.4., and 3.B.5. of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, except as required 

by paragraph (m)(4) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. Doing 

the modification in this paragraph terminates 

the inspections required by paragraphs (g) 

and (i) of this AD. 

(k) Post Modification Inspections 

(1) For airplanes on which the bulkhead 

(support frame) modification has been done 

as specified in Boeing Service Bulletin 747– 

53A2473, dated March 24, 2005; Revision 1, 

dated February 20, 2007; Revision 2, dated 

August 28, 2009; Revision 3, dated July 14, 

2011; or Revision 4, dated December 1, 2011: 

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Federal Register / Vol. 79, No. 1 / Thursday, January 2, 2014 / Proposed Rules 69 

Except as provided by paragraphs (m)(7) and 

(m)(8) of this AD, at the applicable time in 

tables 6, 7, 8, and 9 of paragraph 1.E., 

‘‘Compliance’’ of Boeing Service Bulletin 

747–53A2473, Revision 4, dated December 1, 

2011, do support frame post-modification 

inspections, and open-hole HFEC inspections 

for cracking in the hinge support, and do all 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, except as required 

by paragraph (m)(4). Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspections 

thereafter at the applicable times in tables 6, 

7, 8, and 9 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011. 

(2) For airplanes on which the support 

frame modification has been done as 

specified in Boeing Service Bulletin 747– 

53A2473, Revision 1, dated February 20, 

2007: Except as specified in paragraphs 

(m)(7) and (m)(8) of this AD, at the applicable 

time in tables 4 and 5 of paragraph 1.E., 

‘‘Compliance’’ of Boeing Service Bulletin 

747–53A2473, Revision 4, dated December 1, 

2011, do a one-time general visual inspection 

of the frame web and upper shear deck (floor 

support) chord aft side for fasteners that were 

installed as part of an inner chord repair 

removal; and a one-time general visual 

inspection of the upper forward inner chord, 

frame support fitting and splice fitting, for 

the installation of certain fasteners; and do 

all applicable related investigative and 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, except as required 

by paragraph (m)(4) of this AD. Do all 

applicable related investigative and 

corrective actions at the applicable times 

specified in tables 4 and 5 of paragraph 1.E., 

‘‘Compliance’’ of Boeing Service Bulletin 

747–53A2473, Revision 4, dated December 1, 

2011. 

(3) For airplanes on which the support 

frame modification has been done as 

specified in Boeing Service Bulletin 747– 

53A2473, dated March 24, 2005: Except as 

specified in paragraphs (m)(7) and (m)(8) of 

this AD, at the applicable time in tables 5 and 

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

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, do a one-time 

general visual inspection of the upper 

forward inner chord, frame support fitting, 

and splice fitting for the installation of 

certain fasteners; a one-time general visual 

inspection for any repair installed on the left 

and right side of the aft inner chord; and do 

all applicable related investigative and 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, except as required 

by paragraph (m)(4) of this AD. Do all 

applicable related investigative and 

corrective actions at the applicable times 

specified in tables 5 and 10 of paragraph 1.E., 

‘‘Compliance’’ of Boeing Service Bulletin 

747–53A2473, Revision 4, dated December 1, 

2011. 

(4) For airplanes on which a postmodification inspection was done in 

accordance with paragraph 3.B.8. of Part 1 of 

the Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2473, Revision 3, 

dated July 14, 2011: Except as required by 

paragraphs (m)(7) and (m)(8) of this AD, at 

the applicable time in table 11 of paragraph 

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

Bulletin 747–53A2473, Revision 4, dated 

December 1, 2011, do a one-time surface 

HFEC inspection of the support frame outer 

chord for cracking, in accordance with Part 

1 of the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011. If any 

cracking is found, repair before further flight, 

using a method approved in accordance with 

the procedures specified in paragraph (q) of 

this AD. 

(l) Post-Modification Post-Repair Inspections 

For airplanes on which post-modification 

inspection cracks were repaired by doing the 

installation of an upper or lower corner postmodification web crack repair as specified in 

Boeing Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011: At the 

applicable times specified in tables 6 and 8 

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

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, do a bulkhead 

(support frame) post-repair inspection, and 

do all applicable corrective actions, in 

accordance with paragraph a., b., or c. of Part 

4 of paragraph 3.B.8 of the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2473, Revision 4, dated December 1, 

2011, as applicable, except as required by 

paragraph (m)(4) of this AD. Repeat the 

inspection, thereafter, at the applicable times 

specified in tables 6 and 8 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2473, Revision 4, dated December 1, 

2011. 

(m) Exceptions 

(1) Where Boeing Alert Service Bulletin 

747–53A2427, Revision 7, dated July 19, 

2013, specifies a compliance time after the 

date on Revision 2 of this service bulletin, 

this AD requires compliance within the 

specified compliance time as of August 28, 

2001 (the effective date of AD 2001–15–03, 

Amendment 39–12337 (66 FR 38365, July 24, 

2001)). 

(2) Where Boeing Alert Service Bulletin 

747–53A2427, Revision 7, dated July 19, 

2013, specifies a compliance time after the 

date on Revision 4 of this service bulletin, 

this AD requires compliance within the 

specified compliance time as of August 5, 

2010 (the effective date of AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010)). 

(3) Where Boeing Alert Service Bulletin 

747–53A2427, Revision 7, dated July 19, 

2013, specifies a compliance time after the 

date on Revision 6 or Revision 7 of this 

service bulletin, this AD requires compliance 

within the specified compliance time ‘‘after 

the effective date of this AD.’’ 

(4) If any cracking is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013; or Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011; specifies to contact 

Boeing for appropriate action: Before further 

flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (q) of this AD. 

(5) If, during any inspection required by 

paragraph (g) of this AD, any cracking is 

found in the bonded web doubler, before 

further flight, repair, using a method 

approved in accordance with the procedures 

specified in paragraph (q) of this AD. 

(6) Where Part 1 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2427, Revision 7, dated July 19, 

2013, specifies accomplishing inspections for 

cracks for forward and aft inner chords, 

splice fittings, floor supports, and upper and 

lower web panels, this AD also requires 

doing an open-hole HFEC inspection of the 

bonded web doubler if present. 

(7) Where Boeing Service Bulletin 747– 

53A2473, Revision 4, dated December 1, 

2011, specifies a compliance time after the 

date on Revision 2 of that service bulletin, 

this AD requires compliance within the 

specified compliance time as of August 5, 

2010 (the effective date of AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010)). 

(8) Where Boeing Service Bulletin 747– 

53A2473, Revision 4, dated December 1, 

2011, specifies a compliance time after the 

date on Revision 3 or 4 of that service 

bulletin, this AD requires compliance within 

the specified compliance time ‘‘after the 

effective date of this AD.’’ 

(n) Optional Termination Modification 

Accomplishing the modification of the 

bulkhead at body station 2598, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2837, dated 

July 13, 2012, terminates the requirements of 

paragraphs (g), (h), (i), (j), (k), and (l) of this 

AD, except where Boeing Service Bulletin 

747–53A2837, dated July 13, 2012, specifies 

to contact Boeing for appropriate action: 

Before further flight, repair the crack using a 

method approved in accordance with the 

procedures specified in paragraph (q) of this 

AD. 

(o) Terminating Action for Certain 

Requirements of AD 2010–14–07, 

Amendment 39–16352 (75 FR 38001, July 1, 

2010) 

(1) Accomplishing the inspections, repairs, 

and modification in accordance with Boeing 

Service Bulletin 747–53A2473, Revision 4, 

dated December 1, 2011, is a terminating 

action for the corresponding inspections, 

repairs, and modification at the STA 2598 

support frame required by paragraphs (i), (j), 

(k), (1), (m), (n), (o), (p), (q), (r), (s), (t), (u), 

and (v) of AD 2010–14–07, Amendment 39– 

16352 (75 FR 38001, July 1, 2010). Where 

Boeing Service Bulletin 747–53A2473, 

Revision 4, dated December 1, 2011, specifies 

to contact Boeing for repair instructions, the 

repair instructions must be approved by the 

FAA in accordance with paragraph (q) of this 

AD. All provisions of AD 2010–14–07 that 

are not specifically referenced in this 

paragraph remain fully applicable and must 

be complied with. 

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70 Federal Register / Vol. 79, No. 1 / Thursday, January 2, 2014 / Proposed Rules 

(2) Accomplishing the inspections, repairs 

and interim modification in accordance with 

Boeing Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013, is a 

terminating action for the corresponding 

inspections, repairs and interim modification 

at the STA 2598 bulkhead required by 

paragraphs (i), (j), (o), (s), (t), (u), and (v) of 

AD 2010–14–07, Amendment 39–16352 (75 

FR 38001, July 1, 2010). When Boeing Alert 

Service Bulletin 747–53A2427, Revision 7, 

dated July 19, 2013, specifies to contact 

Boeing for repair data, the repair data must 

be approved by the FAA in accordance with 

paragraph (q) of this AD. All provisions of 

AD 2010–14–07 that are not specifically 

referenced in this paragraph remain fully 

applicable and must be complied with. 

(p) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g), (h), (i), 

and (n)(2) of this AD, if those actions were 

performed before the effective date of this AD 

using Boeing Alert Service Bulletin 747– 

53A2427, Revision 6, dated July 14, 2011, 

provided that the additional actions added in 

Boeing Alert Service Bulletin 747–53A2427, 

Revision 7, dated July 19, 2013, are done 

within the applicable compliance times 

specified in paragraphs (g), (h), and (i) of this 

AD. 

(q) 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 (r)(1) 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. 

(4) Related portions or applicable 

paragraphs of AMOCs approved previously 

for AD 2010–14–07, Amendment 39–16352 

(75 FR 38001, July 1, 2010), are approved as 

AMOCs for the related corresponding 

provisions of paragraphs (g), (h), (i), (j), (k), 

and (l) of this AD. All new actions specified 

in paragraphs (g), (h), (i), (j), (k), and (l) of 

this AD that are not identified in the AMOCs 

must still be done. 

(r) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6428; fax: 425–917– 

6590; email: nathan.p.weigand@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, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

December 20, 2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–31315 Filed 12–31–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1069; Directorate 

Identifier 2013–NM–197–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. 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 

Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, Model CL–600–2D15 

(Regional Jet Series 705) airplanes, 

Model CL–600–2D24 (Regional Jet 

Series 900) airplanes, and Model CL– 

600–2E25 (Regional Jet Series 1000) 

airplanes. This proposed AD was 

prompted by a determination that for 

certain slat system jam-disconnect 

failure cases, the resulting slat skew 

could lead to failure of the eccentric pin 

at the slat track attachment. If the pin 

migrates out of the attachment lugs, this 

could cause certain slat panels to 

disconnect from the wing. This 

proposed AD would require replacing 

certain locking plates with certain antimigration assemblies on certain left and 

right wing slats. We are proposing this 

AD to prevent failure of the eccentric 

pins at the slat track attachment, and 

consequent slat panels disconnecting 

from the wing, leading to the loss of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by February 18, 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Bombardier, 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; email 

thd.crj@aero.bombardier.com; Internet 

http://www.bombardier.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; or in person at the 

Docket Operations office 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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

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–2013–1069; Directorate Identifier 

2013–NM–197–AD’’ at the beginning of 

your comments. We specifically invite 

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