Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations 77379 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0366; Directorate 

Identifier 2011–NM–024–AD; Amendment 

39–18038; AD 2014–24–05] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–300, 747–400, 747– 

400D, and 747SR series airplanes. This 

AD was prompted by a report of a 

cracked reveal made from a casting 

found within a group of airplanes that 

should have machined reveals made 

only from 6061 aluminum. This AD 

requires an inspection to determine the 

material of the number 3 main entry 

door (MED) corner reveal, repetitive 

inspections of certain reveals for 

cracking, and corrective action if 

necessary. This AD also requires 

repetitive inspections for cracking of 

6061 machined aluminum one-piece 

corner reveals, and replacement with 

6061 machined aluminum two-piece 

corner reveals if necessary, which 

terminates certain repetitive 

inspections. We are issuing this AD to 

detect and correct fatigue cracking of the 

lower forward corner reveal of the 

number 3 MEDs, which could lead to 

the door escape slide departing the 

airplane when the door is opened and 

the slide is deployed, and consequent 

injuries to passengers and crew using 

the door escape slide during an 

emergency evacuation. 

DATES: This AD is effective January 28, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 28, 2015. 

ADDRESSES: 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 by searching for 

and locating Docket No. FAA–2013– 

0366; 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 

Docket 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: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6432; fax: 425– 

917–6590; email: bill.ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, 

October 1, 2008). AD 2008–18–07 

applies to certain The Boeing Company 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–300, 

747–400, 747–400D, and 747SR series 

airplanes. The NPRM published in the 

Federal Register on May 8, 2013 (78 FR 

26720). The NPRM was prompted by a 

report of a cracked reveal made from a 

casting found within a group of 

airplanes that should have machined 

reveals made only from 6061 aluminum. 

The NPRM proposed to retain all the 

requirements of AD 2008–18–07. The 

NPRM also proposed to add, for certain 

airplanes, an inspection to determine 

the material of the number 3 MED 

corner reveal, repetitive inspections for 

cracking of 6061 machined aluminum 

one-piece corner reveals, and 

replacement with 6061 machined 

aluminum two-piece corner reveals if 

necessary, which terminates certain 

repetitive inspections. We are issuing 

this AD to detect and correct fatigue 

cracking of the lower forward corner 

reveal of the number 3 MEDs, which 

could lead to the door escape slide 

departing the airplane when the door is 

opened and the slide is deployed, and 

consequent injuries to passengers and 

crew using the door escape slide during 

an emergency evacuation. 

Related AD 

AD 2008–18–07, Amendment 39– 

15664 (73 FR 56960, October 1, 2008), 

requires, for The Boeing Company 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–300, 

747–400, 747–400D, and 747SR series 

airplanes, an inspection to determine 

the material of a number 3 MED corner 

reveal, repetitive inspections of certain 

reveals for cracking, a detailed 

inspection of certain reveals for a sharp 

edge and cracking, and corrective action 

if necessary. AD 2008–18–07 allows 

reveal replacement as an option to 

certain inspections. AD 2008–18–07 was 

prompted by reports of cracking and/or 

a sharp edge in the lower forward corner 

reveal of the number 3 MEDs. AD 2008– 

18–07 refers to Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 

1, dated February 13, 2007, as the 

appropriate source of service 

information for the required actions 

specified in that AD. 

Explanation of Difference in 

Requirements Between the NPRM (78 

FR 26720, May 8, 2013) and This Final 

Rule 

In the NPRM (78 FR 26720, May 8, 

2013), the FAA proposed to supersede 

AD 2008–18–07, Amendment 39–15664 

(73 FR 56960, October 1, 2008), to 

reflect the changes in airplane groups 

specified in revised service information, 

Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010. However, based on 

the comments received on the NPRM, it 

became evident that it was difficult to 

follow the numerous changes between 

Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 1, dated 

February 13, 2007, and Boeing Special 

Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 

2010, as well as in following the 

corresponding actions specified in the 

NPRM. 

There are only two significant 

changes in Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 

2, dated December 22, 2010: (1) 

Airplanes having line numbers 1038 

through 1270 were moved from Group 

2 to Group 4; and (2) for Group 4 

airplanes, there are additional actions. 

Therefore, for clarity, we have 

determined that a less burdensome 

approach is to revise this final rule to 

include only the new actions for Group 

4 airplanes. Instead of superseding AD 

2008–18–07, Amendment 39–15664 (73 

FR 56960, October 1, 2008), this final 

rule is a stand-alone AD, applicable 

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77380 Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations 

only to Group 4 airplanes as identified 

in Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, except for those 

airplanes that have been converted to an 

all-cargo configuration. Airplanes 

identified in the applicability of AD 

2008–18–07 are still required to 

continue to comply with the 

requirements of that AD. 

Since this AD does not supersede AD 

2008–18–07, Amendment 39–15664 (73 

FR 56960, October 1, 2008), paragraphs 

(g) through (m), (p), (q), and (v) of the 

NPRM (78 FR 26720, May 8, 2013) are 

not included in this AD. Also, the 

corresponding paragraph identifiers 

have been redesignated in this final 

rule, as listed in the following table: 

REDESIGNATED PARAGRAPH

IDENTIFIERS

Requirement in the 

proposed AD (78 FR 

26720, May 8, 2013) 

Corresponding requirement in this AD 

paragraph (t) paragraph (g). 

paragraph (s) paragraph (h). 

paragraph (r) paragraph (i). 

paragraph (u) paragraph (j). 

paragraph (n) paragraph (k). 

paragraph (o) paragraph (l). 

paragraph (w) paragraph (n). 

We have also revised paragraphs (n) 

and (o) of the proposed AD (78 FR 

26720, May 8, 2013) (redesignated as 

paragraphs (k) and (l) of this AD) that 

referred to ‘‘AD 2008–18–07.’’ In 

paragraphs (k) and (l) of this AD, we 

have referred to the current service 

information, Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 

2, dated December 22, 2010, instead of 

AD 2008–18–07, Amendment 39–15664 

(73 FR 56960, October 1, 2008), for the 

locations where cast 356 aluminum 

reveals and machined 6061 aluminum 

reveals may not be installed. Paragraphs 

(k) and (l) of this AD state that the parts 

installation prohibition ends the parts 

installation prohibitions specified in 

paragraphs (n) and (o) of AD 2008–18– 

07, Amendment 39–15664 (73 FR 

56960, October 1, 2008). 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (78 FR 26720, 

May 8, 2013) and the FAA’s response to 

each comment. 

Request To Clarify the Cause of the 

Unsafe Condition 

Boeing asked that we clarify the cause 

of the unsafe condition identified in 

paragraph (e) of the proposed AD (78 FR 

26720, May 8, 2013). Boeing stated that 

the report that prompted the proposed 

supersedure of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, 

October 1, 2008), involved a cracked 

casting on an airplane that should have 

machined reveals made from only 6061 

aluminum. 

We agree that the unsafe condition 

should be clarified for the reason 

provided. We have changed the wording 

for the unsafe condition identified in 

the SUMMARY section and in paragraph 

(e) of this final rule to specify that ‘‘This 

new AD was prompted by a report of a 

cracked reveal made from a casting 

found within a group of airplanes that 

should have machined reveals made 

only from 6061 aluminum.’’ We have 

also clarified the Discussion section of 

this final rule to specify that the NPRM 

(78 FR 26720, May 8, 2013) was 

prompted by that report. 

Request To Revise Wording in the 

NPRM (78 FR 26720, May 8, 2013) 

Boeing requested numerous changes 

related to the wording in paragraphs (g), 

(h), (j), (u) and (v) of the NPRM (78 FR 

26720, May 8, 2013). 

We acknowledge the commenter’s 

concerns for clarity. However, as stated 

previously, this AD does not supersede 

AD 2008–18–07, Amendment 39–15664 

(73 FR 56960, October 1, 2008). The 

changes requested by the commenter 

referred to the ‘‘retained’’ paragraphs of 

AD 2008–18–07, which are not restated 

in this AD; therefore, no action is 

necessary in this regard. 

Request To Revise Service Information 

Delta Airlines (Delta) requested that 

Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, be revised prior to 

the issuance of this final rule. Delta 

stated that paragraphs (r) and (s) of the 

proposed AD (78 FR 26720, May 8, 

2013) (redesignated as paragraphs (i) 

and (h) of this AD) are clear and 

understandable; however, when Delta 

reviewed the required actions in Table 

1 of Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, Delta was not able 

to clearly determine which conditions 

were linked with which actions. Delta 

stated that Boeing also agrees that the 

compliance tables of Boeing Special 

Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 

2010, should be clarified for operators’ 

use. 

We disagree with delaying this AD to 

wait for revised service information in 

light of the urgency of the identified 

unsafe condition. As Delta stated, the 

tables contained in Boeing Special 

Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 

2010, are complicated and could be 

misinterpreted; however, we have 

addressed this concern by specifying the 

requirements and clarifying the 

appropriate actions in paragraphs (h) 

and (i) of this AD. When the service 

information is revised, we might 

consider approving it as an alternative 

method of compliance (AMOC) for these 

actions. We have not changed this final 

rule in this regard. 

Request To Address an Error in Service 

Information 

Delta stated that, in the last row under 

the ‘‘Action’’ column of Table 8 of 

paragraph 1.E., Compliance, of Boeing 

Special Attention Service Bulletin 747– 

53–2460, Revision 2, dated December 

22, 2010, there is a reference to ‘‘Table 

9,’’ which does not exist. Delta stated 

that the correct paragraph reference is 

‘‘Paragraph 3.B., Part 2,’’ as confirmed 

in Delta’s correspondence with Boeing. 

Delta requested that Boeing Special 

Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 

2010, be revised prior to the issuance of 

this final rule, or that we address this 

error in this final rule, or, at a 

minimum, address this error in a global 

AMOC. 

We partially agree. We disagree to 

wait for revised service information in 

light of the urgency of the identified 

unsafe condition. However, we agree 

that the reference to Table 9 in 

paragraph 1.E., Compliance, of Boeing 

Special Attention Service Bulletin 747– 

53–2460, Revision 2, dated December 

22, 2010, is incorrect. To address this 

error, we have added a new paragraph 

(m) in this AD to state that, where the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747– 

53–2460, Revision 2, dated December 

22, 2010, specify a post-repair detailed 

inspection in accordance with Table 9, 

this AD requires a detailed inspection in 

accordance with paragraph 3.B., Part 2, 

of the Accomplishment Instructions of 

Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010. When revised 

service information becomes available, 

we might consider approving it as an 

AMOC for the actions required by this 

AD. 

Request To Revise the Proposed AD To 

Include an Inspection for a Sharp Edge 

for Group 4 Airplanes 

Boeing asked that we revise paragraph 

(r)(2) of the proposed AD (78 FR 26720, 

May 8, 2013) (redesignated as paragraph 

(i)(2) of this AD) to include an 

inspection for a potential sharp edge 

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Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations 77381 

common to the reveal. Boeing stated 

that this inspection might be the first 

inspection performed and, therefore, it 

is possible that a sharp edge could be 

found on a machined reveal. 

We do not agree to revise the wording 

of paragraph (i)(2) of this AD 

(designated as paragraph (r)(2) of the 

proposed AD (78 FR 26720, May 8, 

2013)). Paragraph (i)(2) of this AD 

requires, for previously inspected Group 

4 airplanes, a material-type inspection 

to determine if the corner reveal is a 

casting, and, if a casting is found, 

continued inspections or replacement of 

the reveal with a two-piece machined 

reveal. Castings do not have sharp 

edges. Group 4 airplanes that were not 

previously inspected or changed, that 

have corner reveals found not to be 

castings, require inspections for a sharp 

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

have not changed this final rule in this 

regard. 

Request for Alternative Corrective 

Action for Group 4 Airplanes 

Boeing asked that we revise paragraph 

(t)(1) of the proposed AD (78 FR 26720, 

May 8, 2013) (redesignated as paragraph 

(g)(1) of this AD) to allow a weld repair 

for a cracked reveal made from a casting 

on Group 4 airplanes. Boeing stated that 

this would allow operators to repair the 

casting if they cannot obtain a machined 

reveal. 

We agree that paragraph (g)(1) of this 

AD should allow a weld repair as an 

alternative corrective action since this 

was a permitted action for Group 2 

airplanes in AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, 

October 1, 2008). This alternative 

corrective action for Group 4 airplanes 

was contained in Boeing Special 

Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 

2010, but was inadvertently omitted in 

the proposed AD (78 FR 26720, May 8, 

2013). Paragraph (t) of the NPRM is 

redesignated as paragraph (g) in this AD 

and we have revised paragraph (g)(1) by 

adding new paragraphs (g)(1)(i) and 

(g)(1)(ii) in order to allow a weld repair 

as an option to replacing the reveal if 

any cracking is found. In paragraph 

(g)(1)(ii) of this AD we specify repairing 

in accordance with Part 4 of Boeing 

Special Attention Service Bulletin 747– 

53–2460, Revision 2, dated December 

22, 2010. The inspection for cracking 

specified in paragraph (g)(1) of this AD 

is to be repeated thereafter at intervals 

not to exceed 3,000 flight cycles until a 

new two-piece reveal is installed in 

accordance with the requirements of 

paragraph (g)(1)(i) of this AD. 

Request To Reference Service Bulletin 

Information Notices or Revise Service 

Bulletin 

Delta requested that Boeing Service 

Bulletin Information Notice 747–53– 

2460 IN 03, dated March 24, 2011, be 

referenced as an approved deviation 

from Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010. Alternatively, 

Boeing requested that we delay the 

issuance of this final rule until Boeing 

revises Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, to incorporate the 

changes outlined in that information 

notice. 

We partially agree. We agree that 

Boeing Service Bulletin Information 

Notice 747–53–2460 IN 03, dated March 

24, 2011, contains acceptable 

information for the inspection and 

modification mandated in this AD. 

However, we disagree with delaying 

issuance of this final rule until revised 

service information becomes available. 

We have determined that to delay this 

final rule would be inappropriate, 

because the inspections of the number 

3 MED reveals and corrective actions are 

needed to reduce the risk of the 

identified unsafe condition addressed in 

this AD. The information that Boeing 

Service Bulletin Information Notice 

747–53–2460 IN 03, dated March 24, 

2011, clarifies is for reference only and 

is not required to address the identified 

unsafe condition. When revised service 

information becomes available, we 

might consider approving it as an 

AMOC for the actions required by this 

AD. We have made no change to this AD 

in this regard. 

Explanation of Additional Changes 

Made to This Final Rule 

We redesignated paragraphs (r) and 

(r)(2) of the NPRM (78 FR 26720, May 

8, 2013) as paragraphs (i) and (i)(2) of 

this final rule and removed the phrase 

‘‘Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010,’’ from the initial 

compliance times listed in those 

paragraphs. In the proposed AD, we 

stated that the compliance times could 

be calculated from the most recent work 

performed in accordance with Boeing 

Special Attention Service Bulletin 747– 

53–2460, Revision 1, dated February 13, 

2007; or Revision 2, dated December 22, 

2010; but this would introduce an error 

in paragraph (i) of this AD since it 

would require operators to complete the 

inspections required by Boeing Special 

Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 

2010, for a second time, if the reference 

to Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, remained. 

Paragraph (i)(1) of this final rule 

specifies inspections for cracking of any 

corner reveal found to be a one-piece or 

two-piece casting. Boeing Special 

Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 

2010, provides inspection procedures 

for one-piece corner reveals, but not for 

the two-piece corner reveals. Because 

the inspection procedures for the twopiece corner reveals were not included 

in the service information, operators 

would have been unable to comply with 

the proposed requirement to inspect a 

two-piece corner reveal, and in this case 

would have been required to obtain 

approval of an alternative method of 

compliance for this inspection. We have 

therefore revised paragraph (i)(1) of this 

AD to provide the appropriate 

procedures for both scenarios. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

26720, May 8, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 26720, 

May 8, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 166 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

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ESTIMATED COSTS

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

Material type inspection and 

inspection for cracks.

14 work-hours × $85 per hour 

= $1,190 per inspection 

cycle.

$0 $1,190 per inspection cycle ... $197,540 per inspection 

cycle. 

We estimate the following costs to do 

any necessary on-condition actions that 

would be required based on the results 

of the inspections. We have no way of 

determining the number of aircraft that 

might need these actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Corner reveal removal and replacement 17 work-hours × $85 per hour = $1,445 

per inspection cycle.

$9,525 $10,970 per inspection cycle. 

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 

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 adding 

the following new airworthiness 

directive (AD): 

2014–24–05 The Boeing Company: 

Amendment 39–18038; Docket No. 

FAA–2013–0366; Directorate Identifier 

2011–NM–024–AD. 

(a) Effective Date 

This AD is effective January 28, 2015. 

(b) Affected ADs 

Certain requirements of this AD terminate 

certain requirements of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008). 

(c) Applicability 

This AD applies to The Boeing Company 

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

747–200B, 747–200C, 747–300, 747–400, 

747–400D, and 747SR series airplanes, 

certificated in any category, identified as 

Group 4 airplanes in Boeing Special 

Attention Service Bulletin 747–53–2460, 

Revision 2, dated December 22, 2010, except 

airplanes that have been converted to an allcargo configuration. Also, the requirements 

of this AD are applicable when a converted 

airplane operating in an all-cargo 

configuration is converted back to a 

passenger or passenger/cargo configuration. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

cracked reveal made from a casting found 

within a group of airplanes that should only 

have machined reveals made from 6061 

aluminum. We are issuing this AD to detect 

and correct fatigue cracking of the lower 

forward corner reveal of the number 3 main 

entry doors (MEDs), which could lead to the 

door escape slide departing the airplane 

when the door is opened and the slide is 

deployed, and consequent injuries to 

passengers and crew using the door escape 

slide during an emergency evacuation. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Actions for Group 4 Airplanes: Not 

Previously Inspected or Changed 

For Group 4 airplanes identified in Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010, 

that have not been previously inspected or 

changed in accordance with Boeing Special 

Attention Service Bulletin 747–53–2460, 

Revision 1, dated February 13, 2007: Before 

the accumulation of 1,500 total flight cycles, 

or within 1,000 flight cycles after the 

effective date of this AD, whichever occurs 

later, do a material type inspection to 

determine if the lower forward corner reveal 

is made from 6061 machined aluminum plate 

or 356 aluminum casting, in accordance with 

Part 6 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Doing the inspection specified in 

this paragraph terminates the inspections 

required by paragraph (j) of AD 2008–18–07, 

Amendment 38–15664 (73 FR 56960, October 

1, 2008), for that airplane only. 

(1) If, during any inspection required by 

paragraph (g) of this AD, any corner reveal 

is found to be a casting: Before the 

accumulation of 7,000 total flight cycles; 

within 2,000 flight cycles after the effective 

date of this AD; or within 3,000 flight cycles 

after the most recent inspection of the 

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number 3 MED corner reveal was done in 

accordance with Boeing Service Bulletin 

747–53A2378, Revision 4, dated June 10, 

2010; whichever occurs later; do a detailed 

inspection for cracking of the corner reveal, 

in accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

Repeat the inspection for cracking thereafter 

at intervals not to exceed 3,000 flight cycles 

until a new two-piece reveal is installed in 

accordance with the requirements of 

paragraph (g)(1)(i) of this AD. If any cracking 

is found, do the actions specified in 

paragraph (g)(1)(i) or (g)(1)(ii) of this AD. 

(i) Replace the cast reveal with a new 6061 

machined aluminum two-piece corner reveal, 

before further flight, in accordance with Part 

3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. 

(ii) Repair all cracking, before further 

flight, in accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

(2) If, during any inspection required by 

paragraph (g) of this AD, a corner reveal is 

found that is not a casting: Before further 

flight, do a detailed inspection for a sharp 

edge, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010; 

and do a detailed inspection for cracking of 

the corner reveal, in accordance with Part 2 

of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Repeat the inspection for cracking 

thereafter at intervals not to exceed 6,000 

flight cycles until the corner reveal is 

replaced with a 6061 machined aluminum 

two-piece corner reveal in accordance with 

the requirements of paragraph (j) of this AD. 

(i) If any sharp edge is found during any 

inspection required by paragraph (g)(2) of 

this AD, before further flight, rework the 

corner reveal, in accordance with Part 1 of 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

(ii) If any cracking is found during any 

inspection required by paragraph (g)(2) of 

this AD, before further flight, replace the 

corner reveal with a 6061 machined 

aluminum two-piece corner reveal, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

(h) Actions for Previously Inspected Group 

4 Airplanes: Corner Reveal Replaced With 

One-Piece Reveal 

For Group 4 airplanes identified in Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010, 

that have been inspected previously in 

accordance with Boeing Service Bulletin 

747–53–2460, Revision 1, dated February 13, 

2007, and on which the corner reveal has 

been replaced with a one-piece reveal: 

Within 10,000 flight cycles after the date the 

reveal was replaced with a one-piece corner 

reveal, do a detailed inspection for cracking 

of the corner reveal, in accordance with Part 

2 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Repeat the inspection for cracking 

thereafter at intervals not to exceed 6,000 

flight cycles until the corner reveal is 

replaced with a 6061 machined aluminum 

two-piece corner reveal, in accordance with 

the requirements of paragraph (j) of this AD. 

If any cracking is found during any 

inspection required by this paragraph, before 

further flight, replace the one-piece corner 

reveal with a 6061 machined aluminum twopiece corner reveal, in accordance with Part 

3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. 

(i) Actions for Previously Inspected Group 4 

Airplanes: Corner Reveal Not Replaced, or 

Replaced With Two-Piece Reveal 

For Group 4 airplanes identified in Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010, 

that have been inspected previously in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 1, 

dated February 13, 2007; and on which the 

corner reveal either has not been replaced, or 

has been replaced with a two-piece reveal 

that was made by reworking an existing onepiece reveal: Before the accumulation of 

7,000 total flight cycles; within 3,000 flight 

cycles after the most recent inspection or 

rework done in accordance with Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

within 1,000 flight cycles after the effective 

date of this AD; whichever occurs later; do 

a material type inspection to determine if the 

corner reveal is a casting, in accordance with 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

Doing the inspection specified in this 

paragraph terminates the inspections 

required by paragraph (j) of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008), for these airplanes. 

(1) If, during any inspection required by 

paragraph (i) of this AD, any corner reveal is 

found to be a casting: Before further flight, do 

a detailed inspection for cracking of the 

corner reveal. For one-piece reveals, inspect 

in accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010; 

for two-piece reveals, inspect using a method 

approved in accordance with the procedures 

specified in paragraph (n) of this AD. Repeat 

the inspection thereafter at intervals not to 

exceed 3,000 flight cycles until a new twopiece reveal is installed in accordance with 

the requirements of paragraph (i)(1)(i) of this 

AD. If any cracking is found, do the actions 

specified in paragraph (i)(1)(i) or (i)(1)(ii) of 

this AD. 

(i) Replace the cast reveal with a new 6061 

machined aluminum two-piece corner reveal, 

before further flight, in accordance with Part 

3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. 

(ii) Repair all cracking, before further 

flight, in accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

(2) If, during any inspection required by 

paragraph (i) of this AD, any one-piece corner 

reveal is found to be installed and is not a 

casting: Before the accumulation of 10,000 

total flight cycles; or within 6,000 flight 

cycles after the most recent inspection done 

in accordance with Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 1, 

dated February 13, 2007; whichever occurs 

later; do a detailed inspection of the corner 

reveal for cracking, in accordance with Part 

2 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Repeat the inspection for cracking 

thereafter at intervals not to exceed 6,000 

flight cycles until the corner reveal is 

replaced with a 6061 machined aluminum 

two-piece corner reveal. If any cracking is 

found during any inspection required by this 

paragraph, before further flight, replace the 

corner reveal with a 6061 machined 

aluminum two-piece corner reveal, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

(j) Terminating Action for Repetitive 

Inspections 

Installation of a 6061 machined aluminum 

two-piece corner reveal in accordance with 

Part 3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010, terminates the repetitive 

inspections required by paragraphs (g), (h), 

and (i) of this AD. 

(k) Parts Installation Prohibition: (Cast 356 

Aluminum) Reveals 

As of the effective date of this AD, no 

person may install a door lower forward 

corner reveal made of cast 356 aluminum on 

any airplane at a location specified in the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

This parts installation prohibition ends the 

parts installation prohibition specified in 

paragraph (n) of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008), for the airplanes identified in 

paragraph (c) of this AD. 

(l) Parts Installation Limitation: (Machined 

6061 Aluminum) Reveals 

As of the effective date of this AD, no 

person may install a door lower forward 

corner reveal made of machined 6061 

aluminum on any airplane at a location 

specified in the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 2, 

dated December 22, 2010, unless it has been 

confirmed/reworked to be without a sharp 

edge, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing 

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77384 Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

This parts installation prohibition ends the 

parts installation prohibition specified in 

paragraph (o) of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008), for the airplanes identified in 

paragraph (c) of this AD. 

(m) Exceptions to Service Information 

Specifications 

Where Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, specifies a post-repair 

detailed inspection in accordance with Table 

9, this AD requires a detailed inspection in 

accordance with paragraph 3.B., Part 2, of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. 

(n) 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 (o) 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. 

(o) Related Information 

For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917–6590; 

email: bill.ashforth@faa.gov. 

(p) 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. 

(i) Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010. 

(ii) Reserved. 

(3) 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. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

November 19, 2014. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–30132 Filed 12–23–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0072; Directorate 

Identifier 2013–NE–04–AD; Amendment 39– 

18017; AD 2014–23–01] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Division Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that 

published in the Federal Register. That 

AD applies to all Pratt & Whitney 

Division (PW) PW4074, PW4074D, 

PW4077, PW4077D, PW4084D, 

PW4090, and PW4090–3 turbofan 

engine models with certain second-stage 

high-pressure turbine (HPT) air seals 

installed. The time required to perform 

the initial eddy current inspection (ECI) 

in the Compliance section is incorrect. 

This document corrects that error. In all 

other respects, the original document 

remains the same. 

DATES: This final rule is effective on 

December 26, 2014. The effective date of 

AD 2014–23–01, Amendment 39–18017 

(79 FR 69369, November 21, 2014) 

remains December 26, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 17, 2013 (78 FR 49111, 

August 13, 2013). 

ADDRESSES: 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: JoAnn Theriault, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7105; fax: 781–238– 

7199; email: jo-ann.theriault@faa.gov. 

SUPPLEMENTARY INFORMATION: AD 2014– 

23–01, Amendment 39–18017 (79 FR 

69369, November 21, 2014), requires 

initial and repetitive inspections for 

cracks in second-stage HPT air seals, the 

removal of the mating hardware if the 

second-stage HPT air seal is found with 

a through-crack, and a mandatory 

terminating action for all PW PW4074, 

PW4074D, PW4077, PW4077D, 

PW4084D, PW4090, and PW4090–3 

turbofan engine models with certain 

second-stage HPT air seals installed. 

As published, the time required to 

perform the initial ECI in the 

Compliance section is incorrect. AD 

2014–23–01, paragraph (e)(2)(i), requires 

an initial ECI for cracks within 1,000 

cycles-in-service after September 17, 

2013, or before further flight, whichever 

occurs later. That compliance time is 

more restrictive than intended and will 

likely ground airplanes. The intent was 

to require an initial ECI for cracks before 

reaching 2,200 cycles since new, or 

within 1,000 cycles-in-service after 

September 17, 2013, or before further 

flight, whichever occurs later. 

No other part of the preamble or 

regulatory information has been 

changed. 

The effective date of AD 2014–23–01 

remains December 26, 2014. 

Correction of Regulatory Text 

§ 39.13 [Corrected] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2013–15–09, Amendment 39–17525 (78 

FR 49111, August 13, 2013), and adding 

the following new AD: 

2014–23–01 Pratt & Whitney Division: 

Amendment 39–18017; Docket No. 

FAA–2013–0072; Directorate Identifier 

2013–NE–04–AD. 

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