Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules 56407 

shock injury to persons contacting the 

cockpit door. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Door Modification and Installation 

Within 24 months after the effective date 

of this AD, modify the cockpit door frame 

structure and install bonding-leads to the 

upper cockpit door frame, in accordance with 

the Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 

(1) Airbus Service Bulletin A330–25–3534, 

Revision 01, dated October 23, 2014. (2) 

Airbus Service Bulletin A340–25–4349, 

Revision 01, dated October 27, 2014. (3) 

Airbus Service Bulletin A340–25–5212, 

Revision 01, dated October 27, 2014. 

(h) Cover Plate Modification of the Upper 

Flight Deck Door 

Except for airplanes on which Airbus 

Modification 52869 or Modification 53292 

has been embodied in production: Before or 

concurrently with accomplishing the 

modification required by paragraph (g) of this 

AD, modify the upper cockpit door plate 

cover, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (h)(1), (h)(2), and (h)(3) of this 

AD. 

(1) Airbus Service Bulletin A330–25–3534, 

Revision 01, dated October 23, 2014. (2) 

Airbus Service Bulletin A340–25–4349, 

Revision 01, dated October 27, 2014. (3) 

Airbus Service Bulletin A340–25–5212, 

Revision 01, dated October 27, 2014. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. In accordance with 

14 CFR 39.19, send your request to your 

principal inspector or local Flight Standards 

District Office, as appropriate. If sending 

information directly to the International 

Branch, send it to ATTN: Vladimir Ulyanov, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; fax 

425–227–1149. Information may be emailed 

to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0037, dated 

March 2, 2015, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2015–3631. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. You may 

view this 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 

September 11, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–23409 Filed 9–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0774; Directorate 

Identifier 2013–NM–154–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

that proposed to supersede AD 2006– 

22–15 for all 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. AD 2006–22–15 requires 

repetitive inspections for cracking of 

certain panel webs and stiffeners of the 

nose wheel well (NWW), and corrective 

actions if necessary; and replacement of 

certain panels with new panels, which 

terminates the repetitive inspections. 

The notice of proposed rulemaking 

(NPRM) proposed to reduce a 

compliance time and add certain 

inspections and applicable repair. The 

NPRM was prompted by reports of 

fatigue cracking in the panel webs and 

stiffeners of the NWW found prior to the 

inspection threshold of AD 2006–22–15. 

This action revises the NPRM by 

specifying a repetitive inspection 

interval for a certain NWW area 

inspection. We are proposing this 

SNPRM to prevent fatigue cracking of 

the NWW side and top panels, which 

could result in a NWW depressurization 

event severe enough to reduce the 

structural integrity of the fuselage. 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 November 2, 2015. 

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 proposed 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 


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availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0774. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0774; 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: 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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0774; Directorate Identifier 

2013–NM–154–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 supersede AD 2006–22–15, 

Amendment 39–14812 (71 FR 64884, 

November 6, 2006). AD 2006–22–15 

applies to all 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. The NPRM published 

in the Federal Register on November 17, 

2014 (79 FR 68388). The NPRM was 

prompted by reports of fatigue cracking 

in the panel webs and stiffeners of the 

NWW found prior to the inspection 

threshold of AD 2006–22–15. The 

NPRM proposed to continue to require 

repetitive inspections for cracking of 

certain panel webs and stiffeners of the 

NWW, and corrective actions if 

necessary. The NPRM also proposed to 

continue to require replacing certain 

panels with new panels, which would 

terminate the repetitive inspections. The 

NPRM proposed to reduce a compliance 

time and add certain inspections and 

applicable repair. 

Actions Since Previous NPRM (79 FR 

68388, November 17, 2014) Was Issued 

Since we issued the NPRM (79 FR 

68388, November 17, 2014), we have 

determined that it is necessary to revise 

the NPRM by specifying a certain 

repetitive inspection interval for Area 2 

for airplanes with less than 15,000 total 

flight cycles. This interval is not clearly 

indicated in table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service 

Bulletin 747–53A2465, Revision 5, 

dated July 11, 2013, and was not 

specifically stated in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following Boeing 

service information. Refer to this service 

information for information on the 

procedures and compliance times. 

• Boeing Service Bulletin 747– 

53A2465, Revision 5, dated July 11, 

2013, which describes procedures for 

inspections for cracks of certain top and 

sidewall panel webs and stiffeners of 

the NWW; and repairs. 

• Boeing Service Bulletin 747– 

53A2562, Revision 3, dated July 11, 

2013. This service bulletin describes 

procedures for replacement of the side 

and top panel webs and certain 

stiffeners of the NWW; an inspection for 

cracks in attaching structural elements 

that are common to the removed top 

panel and side panels; repetitive postmodification inspections for cracks in 

the top and side panel webs and 

stiffeners; and contacting Boeing for 

repairs. 

• Boeing Alert Service Bulletin 747– 

53A2808, dated November 30, 2012. 

This service bulletin describes 

procedures for replacement of the side 

and top panel webs, support beams, and 

stiffeners of the NWW; an inspection for 

cracks of the attaching structural 

elements that are common to the 

removed top and side panels of the 

NWW; repetitive post-modification 

inspections for cracks in the top and 

side panel webs and stiffeners; and 

contacting Boeing for repairs. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section of 

this AD. 

Comments 

We gave the public the opportunity to 

comment on the NPRM (79 FR 68388, 

November 17, 2014). The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Requests To Specify Repetitive 

Inspection Interval for Area 2 

United Airlines (UAL) and United 

Parcel Service (UPS) requested that we 

specify the repetitive inspection interval 

for Area 2 for airplanes with less than 

15,000 total flight cycles. The 

commenters point out that this is not 

clearly indicated in table 1 of paragraph 

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

Bulletin 747–53A2465, Revision 5, 

dated July 11, 2013, and was not 

specifically stated in the NPRM (79 FR 

68388, November 17, 2014). The 

commenters stated that Boeing has 

issued a service bulletin information 

notice to inform operators that the 

repetitive inspection interval for Area 2 

should be 1,000 flight cycles. 

We agree with the commenters’ 

requests to specify the repeat interval 

for Area 2. We have revised paragraph 

(g) of this SNPRM to specify this 

interval. 

Request To Specify Repair Procedures 

UAL asked whether paragraph (h)(3) 

of the proposed AD (79 FR 68388, 

November 17, 2014) should be revised 

to specify repair requirements for each 

area, instead of contacting the FAA or 

the Boeing Commercial Airplanes 

Organization Designation Authorization 

(ODA) for repair instructions for any 

cracking or damage found during the 

inspection specified in paragraph (g) of 

the proposed AD. UAL explained that 

Boeing Service Bulletin 747–53A2465, 

Revision 5, dated July 11, 2013, 

specifies repairing web cracks in Area 1 

or 2 per the ‘‘747 Structural Repair 

Manuals.’’ 

We agree to provide clarification. The 

intent of paragraph (h)(3) of this SNPRM 

is to make sure that for those conditions 

for which Boeing Service Bulletin 747– 

53A2465, Revision 5, dated July 11, 

2013, specifies that the operator is to 

contact Boeing for repair data, the 

operator would be required to use a 

repair method approved by the FAA or 

Boeing Commercial Airplanes ODA. We 

have not changed this SNPRM in this 

regard. 


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Request To Clarify Certain Compliance 

Times 

UAL requested clarification of why 

the footnotes in table 2 of paragraph 

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

Bulletin 747–53A2465, Revision 5, 

dated July 11, 2013, reverted back to 

6,000 flight cycles for Area 3 

inspections for cracks of the sidewall 

panel and top panel stiffeners. UAL also 

asked why the 6,000-flight-cycle time is 

just for the first repeat inspection and 

then Area 3 has to be reinspected every 

1,500 flight cycles thereafter. 

We agree that clarification is 

necessary. Paragraph (f)(2) of AD 2006– 

22–15, Amendment 39–14812 (71 FR 

64884, November 6, 2006), specifies the 

6,000-flight-cycle and 1,500-flight-cycle 

inspection times. Boeing Service 

Bulletin 747–53A2465, Revision 5, 

dated July 11, 2013, states that 

inspections and corrective actions 

defined therein are an alternative 

method of compliance (AMOC) to the 

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

(i), and (j) of AD 2006–22–15. In order 

to be approved as an AMOC to certain 

requirements of AD 2006–22–15, Boeing 

Service Bulletin 747–53A2465, Revision 

5, dated July 11, 2013, must state the 

compliance times required by AD 2006– 

22–15 to address the identified unsafe 

condition. We have not changed this 

SNPRM in this regard. 

Request To Revise Certain Headers To 

Clarify Intent of Requirements 

Boeing requested that we revise the 

heading of paragraph (g) of the proposed 

AD (79 FR 68388, November 17, 2014) 

to either change ‘‘Repetitive 

Inspections’’ to ‘‘Initial and Repetitive 

Inspections’’ or delete ‘‘Repetitive.’’ 

Boeing stated that paragraph (g) of the 

proposed AD contains both initial and 

repetitive inspections. 

Boeing requested that we delete 

‘‘Repetitive’’ from the headings of 

paragraphs (j) and (m) of the proposed 

AD (79 FR 68388, November 17, 2014). 

Boeing stated that paragraphs (j) and (m) 

of the proposed AD specify not only 

repetitive inspections, but also the 

initial post-modification inspections. 

We agree that clarification is 

necessary. We do not consider that the 

term ‘‘repetitive’’ necessarily excludes 

the initial action. An action cannot be 

repeated without accomplishment of the 

initial action. Many existing ADs refer 

to ‘‘repetitive’’ actions, which we intend 

as including the initial action. In 

addition, changing ‘‘Repetitive 

Inspections’’ to simply ‘‘Inspections’’ 

could result in the misinterpretation 

that multiple different inspections are 

required. We have not changed this 

SNPRM regarding this issue. 

Request To Clarify Inspection Location 

Boeing requested that, at the end of 

paragraph (g)(3) of the proposed AD (79 

FR 68388, November 17, 2014), we add 

‘‘of the NWW (specified as Area 1 and 

Area 2 in Boeing Service Bulletin 747– 

53A2465, Revision 5, dated July 11, 

2013)’’ for the ultrasonic inspection. 

We agree with the commenter’s 

request. This revision will make the 

wording in paragraph (g)(3) of this 

proposed AD consistent with the 

wording of each of the areas specified in 

paragraphs (g)(1) and (g)(2) of this 

proposed AD. We have revised 

paragraph (g)(3) of this proposed AD 

accordingly. 

Request To Add New AMOC Limitation 

Boeing requested that we add a new 

paragraph (p)(6) to the NPRM (79 FR 

68388, November 17, 2014), which 

would state that ‘‘New provisions 

(inspection threshold and interval) in 

this AD must be complied with as given 

in this AD.’’ Boeing stated that this 

statement will make it clear that prior 

AMOCs do not exempt the operators 

from compliance with new 

requirements added by this new 

proposed AD. Boeing also stated that the 

wording of ‘‘corresponding provisions’’ 

in paragraph (p)(4) of the proposed AD 

(79 FR 68388, November 17, 2014) 

might not be precise enough, when ADs 

get superseded and paragraphs change. 

Boeing explained that adding this 

statement will reduce the ambiguity of 

paragraphs (o) and (p) of the proposed 

AD. 

We partially agree with the 

commenter’s request. We have revised 

paragraph (p)(4) of this proposed AD to 

state that AMOC actions approved 

previously for AD 2006–22–15, 

Amendment 39–14812 (71 FR 64884, 

November 6, 2006), are approved as 

AMOCs for the corresponding actions of 

this AD. The compliance times in 

AMOCs approved previously for AD 

2006–22–15 are not approved for the 

corresponding actions and compliance 

times in this AD. We have removed 

paragraph (p)(5) of this proposed AD as 

it is no longer necessary. We consider 

this language to be sufficiently clear. 

Adding the commenter’s requested 

language would be redundant to the 

language specified in revised paragraph 

(p)(4) of this proposed AD. 

Requests for Certain Editorial Changes 

Boeing noted that paragraph (m) of 

the proposed AD (79 FR 68388, 

November 17, 2014) incorrectly referred 

to paragraphs ‘‘(l)(1), (l)(2), and (l)(3).’’ 

Boeing asked that we change these 

references to ‘‘(m)(1), (m)(2), and 

(m)(3).’’ 

Boeing requested that we correct the 

AD citation in paragraph (o)(1)(i) of the 

proposed AD (79 FR 68388, November 

17, 2014). Boeing stated that the 

identified effective date of January 27, 

2005, is for AD 2004–25–23, 

Amendment 39–13911 (69 FR 76839, 

December 23, 2004); not AD 2005–09– 

02, Amendment 39–14070 (70 FR 

21141, April 25, 2005; corrected May 

25, 2005, 70 FR 29940)); as stated in the 

NPRM. 

Boeing requested that we correct the 

date of Boeing Service Bulletin 747– 

53A2465, Revision 4, from February 25, 

2004, to February 24, 2005, in paragraph 

(o)(2) of the proposed AD (79 FR 68388, 

November 17, 2014). 

UPS requested that we revise 

paragraph (p)(1) of the proposed AD (79 

FR 68388, November 17, 2014) to 

correct the paragraph identifier for the 

contact person, which should be 

paragraph ‘‘(q)(1).’’ 

We agree with the requests and have 

revised this SNPRM accordingly. 

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 

this same type design. Certain changes 

described above expand the scope of the 

NPRM (79 FR 68388, November 17, 

2014). 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 This SNPRM 

Although this proposed AD does not 

explicitly restate certain requirements of 

AD 2006–22–15, Amendment 39–14812 

(71 FR 64884, November 6, 2006), this 

proposed AD would retain all of the 

requirements of AD 2006–22–15. 

The requirements specified in 

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

AD 2006–22–15, Amendment 39–14812 

(71 FR 64884, November 6, 2006), are 

referenced in Boeing Service Bulletin 

747–53A2465, Revision 5, dated July 11, 

2013, which, in turn, is referenced in 

paragraphs (g) and (h)(3) of this 

proposed AD. 

The requirement specified in 

paragraph (n) of AD 2006–22–15, 

Amendment 39–14812 (71 FR 64884, 

November 6, 2006), is referenced in 

Boeing Service Bulletin 747–53A2562, 

Revision 3, dated July 11, 2013, which, 

in turn, is referenced in paragraph (i) of 

this proposed AD. 


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For Group 2 airplanes identified in 

Boeing Service Bulletin 747–53A2562, 

Revision 1, dated July 28, 2005, and 

certain airplanes not identified in 

Boeing Service Bulletin 747–53A2562, 

Revision 1, dated July 28, 2005, the 

requirement specified in paragraph (o) 

of AD 2006–22–15, Amendment 39– 

14812 (71 FR 64884, November 6, 2006), 

to accomplish a repair using a method 

approved by the FAA is now specified 

in paragraph (i) of this proposed AD. 

However, for these airplanes, one 

method of compliance for 

accomplishing the replacement is 

Boeing Service Bulletin 747–53A2562, 

Revision 3, dated July 11, 2013. 

Therefore, we have referred to Boeing 

Service Bulletin 747–53A2562, Revision 

3, dated July 11, 2013, in paragraph (i) 

of this proposed AD. Operators may still 

request an alternative method of 

compliance (AMOC) using the 

procedures provided in paragraph (p) of 

this AD. 

For certain other airplanes not 

identified in Boeing Service Bulletin 

747–53A2562, Revision 1, dated July 28, 

2005, the requirement specified in 

paragraph (o) of AD 2006–22–15, 

Amendment 39–14812 (71 FR 64884, 

November 6, 2006), to accomplish a 

repair using a method approved by the 

FAA is now specified in paragraph (l) of 

this proposed AD. However, for these 

airplanes, one method of compliance for 

accomplishing the replacement is 

Boeing Alert Service Bulletin 747– 

53A2808, dated November 30, 2012. 

Therefore, we have referred to Boeing 

Alert Service Bulletin 747–53A2808, 

dated November 30, 2012, in paragraph 

(l) of this proposed AD. Operators may 

still request an AMOC using the 

procedures provided in paragraph (p) of 

this AD. 

This proposed AD would require 

accomplishing the actions specified in 

the service information identified 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ Refer to 

this service information for information 

on the procedures and compliance 

times. 

The phrase ‘‘related investigative 

actions’’ is used in this proposed AD. 

‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary actions, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

Differences Between the Proposed AD 

and the Service Information 

For airplanes with fewer than 15,000 

total flight cycles, Boeing Service 

Bulletin 747–53A2465, Revision 5, 

dated July 11, 2013, recommends, in 

part, accomplishing a detailed 

inspection before the accumulation of 

13,000 total flight cycles. However, we 

have determined that the 13,000-totalflight-cycle compliance time is 

insufficient to address the identified 

unsafe condition soon enough to ensure 

an adequate level of safety for the 

affected fleet. Instead, we are proposing 

a compliance time of 10,000 total flight 

cycles. In developing an appropriate 

compliance time for this detailed 

inspection, we considered the degree of 

urgency associated with the subject 

unsafe condition, and the fact that we 

have received a report of a 13-inch crack 

adjacent to a 2-inch crack in the NWW 

right-hand side panel on an airplane 

with 11,428 total flight cycles. This 

difference has been coordinated with 

The Boeing Company. 

Boeing Service Bulletin 747– 

53A2465, Revision 5, dated July 11, 

2013; Boeing Service Bulletin 747 

53A2562, Revision 3, dated July 11, 

2013; and Boeing Alert Service Bulletin 

747–53A2808, dated November 30, 

2012; specify to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

proposed AD would require repairing 

those conditions in one of the following 

ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes ODA whom we 

have authorized to make those findings. 

Explanation of Compliance Time 

The compliance time for the 

modification specified in paragraphs (i) 

and (l) of this proposed AD for 

addressing widespread fatigue damage 

(WFD) was established to ensure that 

discrepant structure is modified before 

WFD develops in airplanes. Standard 

inspection techniques cannot be relied 

on to detect WFD before it becomes a 

hazard to flight. We will not grant any 

extensions of the compliance time to 

complete any AD-mandated service 

bulletin related to WFD without 

extensive new data that would 

substantiate and clearly warrant such an 

extension. 

Costs of Compliance 

We estimate that this proposed AD 

affects 255 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 

Inspections [actions retained from AD 2006– 

22–15, Amendment 39–14812 (71 FR 

64884, November 6, 2006)].

119 work-hours × $85 

per hour = $10,115 

per inspection cycle.

$0 ........................ $10,115 per inspection 

cycle.

$2,579,325 per inspection cycle. 

Modification [actions retained from AD 2006– 

22–15, Amendment 39–14812 (71 FR 

64884, November 6, 2006)].

Up to 1,346 work-hours 

× $85 per hour = 

$114,410.

Up to $144,248 ... Up to $258,658 ........... Up to $65,957,790. 

Post-modification Inspections [new proposed 

action].

119 work-hours × $85 

per hour = $10,115 

per inspection cycle.

$0 ........................ $10,115 per inspection 

cycle.

$2,579,325 per inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition 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, 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules 56411 

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, 

(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– 

2014–0774; Directorate Identifier 2013– 

NM–154–AD. 

(a) Comments Due Date 

We must receive comments by November 

2, 2015. 

(b) Affected ADs 

This AD replaces AD 2006–22–15, 

Amendment 39–14812 (71 FR 64884, 

November 6, 2006). 

(c) Applicability 

This AD applies to all Boeing 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. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by multiple reports 

of cracking in the nose wheel well (NWW) 

top panel and side panel webs and stiffeners 

caused by fatigue. We are issuing this AD to 

prevent fatigue cracking of the NWW side 

and top panels, which could result in a 

NWW depressurization event severe enough 

to reduce the structural integrity of the 

fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections and Corrective 

Actions With New Compliance Times 

Except as specified in paragraphs (h)(1) 

and (h)(2) of this AD, at the applicable time 

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

Boeing Service Bulletin 747–53A2465, 

Revision 5, dated July 11, 2013: Do the 

actions specified in paragraphs (g)(1), (g)(2), 

and (g)(3) of this AD, and do all applicable 

related investigative and corrective actions; 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2465, Revision 5, dated July 11, 2013, 

except as specified in paragraph (h)(3) of this 

AD. Do all applicable related investigative 

and corrective actions before further flight. 

Repeat the inspections specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD 

thereafter at the applicable intervals specified 

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

Service Bulletin 747–53A2465, Revision 5, 

dated July 11, 2013. The repetitive interval 

for the inspection of Area 2 specified in table 

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

Service Bulletin 747–53A2465, Revision 5, 

dated July 11, 2013, is 1,000 flight cycles. In 

table 2 and table 3 in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2465, Revision 5, dated July 11, 

2013, the date ‘‘January 27, 2005’’ is the 

effective date of AD 2004–25–23, 

Amendment 39–13911 (69 FR 76839, 

December 23, 2004); and the date ‘‘May 10, 

2005’’ is the effective date of AD 2005–09– 

02, Amendment 39–14070 (70 FR 21141, 

April 25, 2005; corrected May 25, 2005 (70 

FR 29940)). 

(1) Do an external detailed inspection for 

cracks of the top and sidewall panel webs of 

the NWW (specified as Area 1 and Area 2 in 

Boeing Service Bulletin 747–53A2465, 

Revision 5, dated July 11, 2013). 

(2) Do internal detailed and surface high 

frequency eddy current (HFEC) inspections 

for cracks of the sidewall panel and top panel 

stiffeners of the NWW (specified as Area 3 in 

Boeing Service Bulletin 747–53A2465, 

Revision 5, dated July 11, 2013). 

(3) Do an external detailed and ultrasonic 

testing (UT) inspection for cracks of the top 

and sidewall panel webs of the NWW 

(specified as Area 1 and Area 2 in Boeing 

Service Bulletin 747 -53A2465, Revision 5, 

dated July 11, 2013). 

(h) Exceptions to Boeing Service Bulletin 

747–53A2465, Revision 5, dated July 11, 

2013 

(1) Table 1 in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2465, Revision 5, dated July 11, 

2013, applies to airplanes with less than 

15,000 total flight cycles ‘‘as of the Revision 

5 date of this service bulletin.’’ For this AD, 

however, table 1 applies to airplanes with the 

specified total flight cycles as of the effective 

date of this AD. 

(2) Table 1 in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2465, Revision 5, dated July 11, 

2013, specifies a compliance time of ‘‘13,000 

total flight-cycles,’’ or ‘‘within 1,000 flights 

cycles after the Revision 5 date of this service 

bulletin,’’ whichever occurs later. This AD 

requires compliance before the accumulation 

of 10,000 total flight cycles or within 1,000 

flight cycles after the effective date of this 

AD, whichever occurs later. 

(3) If any cracking or damage is found 

during any inspection required by paragraph 

(g) of this AD, and Boeing Service Bulletin 

747–53A2465, Revision 5, dated July 11, 

2013, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair the cracking or damage using a method 

approved in accordance with the procedures 

specified in paragraph (p) of this AD. 

(i) NWW Modification 

For airplanes identified in Boeing Service 

Bulletin 747–53A2562, Revision 3, dated July 

11, 2013: At the applicable time specified in 

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

Service Bulletin 747–53A2562, Revision 3, 

dated July 11, 2013, replace the left-side, 

right-side, and top panels of the NWW, as 

applicable, with new panels, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2562, 

Revision 3, dated July 11, 2013. As of the 

effective date of this AD, concurrently with 

doing the replacement specified in Boeing 

Service Bulletin 747–53A2562, Revision 3, 

dated July 11, 2013, do a detailed inspection 

for any cracks or damage (including, but not 

limited to, dents and corrosion) in all 

attaching structural elements that are 

common to the removed top panel and side 

panels, as applicable, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2562, Revision 3, 

dated July 11, 2013. If any crack or damage 

is found, before further flight, repair the 

cracking or damage using a method approved 

in accordance with the procedures specified 

in paragraph (p) of this AD. In paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2562, Revision 3, dated July 11, 

2013, the date ‘‘December 11, 2006,’’ is the 


tkelley on DSK3SPTVN1PROD with PROPOSALS
56412 Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules 

effective date of AD 2006–22–15, 

Amendment 39–14812 (71 FR 64884, 

November 6, 2006). 

(j) Repetitive Post-Modification Inspections 

For airplanes on which the replacement 

specified in paragraph (i) of this AD has been 

done: Except as required by paragraph (k) of 

this AD, at the applicable time specified in 

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

Service Bulletin 747–53A2562, Revision 3, 

dated July 11, 2013, do the actions specified 

in paragraphs (j)(1), (j)(2), and (j)(3) of this 

AD. If any crack is found: Before further 

flight, repair the cracking using a method 

approved in accordance with the procedures 

specified in paragraph (p) of this AD. Repeat 

the inspections specified in paragraphs (j)(1), 

(j)(2), and (j)(3) of this AD thereafter at the 

applicable intervals specified in paragraph 

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

Bulletin 747–53A2562, Revision 3, dated July 

11, 2013. 

(1) Do an external detailed inspection for 

cracks in the side panel webs, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2562, 

Revision 3, dated July 11, 2013. 

(2) Do an internal detailed inspection and 

high frequency eddy current (HFEC) 

inspection for cracks in the top and side 

panel stiffeners, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2562, Revision 3, 

dated July 11, 2013. 

(3) Do an external detailed inspection for 

cracks in the top panel web, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2562, 

Revision 3, dated July 11, 2013. 

(k) Exception to Boeing Service Bulletin 747– 

53A2562, Revision 3, Dated July 11, 2013 

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

Boeing Service Bulletin 747–53A2562, 

Revision 3, dated July 11, 2013, specifies a 

compliance time relative to the ‘‘Revision 3 

date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(l) NWW Modification for Certain Airplanes 

For airplanes identified in Boeing Alert 

Service Bulletin 747–53A2808, dated 

November 30, 2012: At the applicable time 

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

Boeing Alert Service Bulletin 747–53A2808, 

dated November 30, 2012, replace the left 

side, right side, and top panels of the NWW, 

as applicable, with new panels, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2808, dated November 30, 2012. 

Concurrently with doing the replacement 

specified in this paragraph, do a detailed 

inspection for cracks of the attaching 

structural elements that are common to the 

removed top, left-side, and right-side panels 

of the NWW, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2808, dated 

November 30, 2012. If any crack is found, 

before further flight, repair the cracking using 

a method approved in accordance with the 

procedures specified in paragraph (p) of this 

AD. 

(m) Repetitive Post-Modification Inspections 

for Certain Airplanes 

For airplanes on which the replacement 

specified in paragraph (l) of this AD has been 

done: At the applicable time specified in 

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

Alert Service Bulletin 747–53A2808, dated 

November 30, 2012, do the actions specified 

in paragraphs (m)(1), (m)(2), and (m)(3) of 

this AD. If any crack is found: Before further 

flight, repair the cracking using a method 

approved in accordance with the procedures 

specified in paragraph (p) of this AD. Repeat 

the inspections specified in paragraphs 

(m)(1), (m)(2), and (m)(3) of this AD 

thereafter at the applicable intervals specified 

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

Alert Service Bulletin 747–53A2808, dated 

November 30, 2012. 

(1) Do an external detailed inspection for 

cracks in the side panel webs, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2808, 

dated November 30, 2012. 

(2) Do an internal detailed inspection and 

HFEC inspection for cracks in the top and 

side panel stiffeners, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2808, dated 

November 30, 2012. 

(3) Do an external detailed inspection for 

cracks in the top panel web, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2808, 

dated November 30, 2012. 

(n) Terminating Action for Certain 

Repetitive Inspections 

Replacing the left side, right side, and top 

panels of the NWW with new panels as 

specified in paragraph (i) or (l) of this AD 

terminates the repetitive inspections required 

by paragraph (g) of this AD. 

(o) Credit for Previous Actions 

(1) This paragraph restates the credit given 

in paragraph (k) of AD 2006–22–15, 

Amendment 39–14812 (71 FR 64884, 

November 6, 2006). 

(i) This paragraph provides credit for the 

actions required by paragraph (g)(1) of this 

AD, if those actions were performed before 

January 27, 2005 (the effective date of AD 

2004–25–23, Amendment 39–13911 (69 FR 

76839, December 23, 2004)), using Boeing 

Alert Service Bulletin 747–53A2465, dated 

April 5, 2001, which is not incorporated by 

reference in this AD. 

(ii) This paragraph provides credit for 

actions required by paragraphs (g)(1) and 

(g)(2) of this AD, if those actions were 

performed before December 11, 2006 (the 

effective date of AD 2006–22–15, 

Amendment 39–14812 (71 FR 64884, 

November 6, 2006)), using a service bulletin 

identified in paragraph (o)(1)(ii)(A), 

(o)(1)(ii)(B), or (o)(1)(ii)(C) of this AD, which 

are not incorporated by reference in this AD. 

(A) Boeing Alert Service Bulletin 747– 

53A2465, Revision 1, dated October 16, 2003. 

(B) Boeing Alert Service Bulletin 747– 

53A2465, Revision 2, dated November 11, 

2004. 

(C) Boeing Alert Service Bulletin 747– 

53A2465, Revision 3, dated December 23, 

2004. 

(2) This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 747–53A2465, Revision 4, 

dated February 24, 2005, which is not 

incorporated by reference in this AD. 

(3) This paragraph provides credit for the 

actions required by paragraphs (i) and (j) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Service Bulletin 747–53A2562, 

Revision 1, dated July 28, 2005; or Boeing 

Service Bulletin 747–53A2562, Revision 2, 

dated May 31, 2007; which are not 

incorporated by reference in this AD. 

(p) 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 (q)(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 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) AMOC actions approved previously for 

AD 2006–22–15, Amendment 39–14812 (71 

FR 64884, November 6, 2006), are approved 

as AMOCs for the corresponding actions of 

this AD. The compliance times in AMOCs 

approved previously for AD 2006–22–15 are 

not approved for the corresponding actions 

and compliance times in this AD. 

(q) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6432; fax: 425– 

917–6590; email: Bill.Ashforth@faa.gov. 

(2) For service information identified in 

this AD, 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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules 56413 

Issued in Renton, Washington, on 

September 1, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–23420 Filed 9–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3633; Directorate 

Identifier 2014–NM–097–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Fokker Services B.V. Model F.27 Mark 

200, 300, 400, 500, 600, and 700 

airplanes. This proposed AD was 

prompted by a design review conducted 

by Fokker Services B.V. that indicated 

no controlled bonding provisions were 

present on many critical locations 

outside the fuel tank or connected to the 

fuel tank wall. This proposed AD would 

require installing the additional bonding 

provisions, and revising the 

maintenance or inspection program, as 

applicable, by incorporating fuel 

airworthiness limitation items and 

critical design configuration control 

limitations. We are proposing this AD to 

prevent an ignition source in the fuel 

tank vapor space, which could result in 

a fuel tank explosion and consequent 

loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 2, 2015. 

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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Fokker 

Services B.V., Technical Services Dept., 

P.O. Box 1357, 2130 EL Hoofddorp, the 

Netherlands; telephone +31 (0)88–6280– 

350; fax +31 (0)88–6280–111; email 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.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–2015– 

3633; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–3633; Directorate Identifier 

2014–NM–097–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0100, dated April 30, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Fokker 

Services B.V. Model F.27 Mark 200, 300, 

400, 500, 600, and 700 airplanes. The 

MCAI states: 

Prompted by an accident * * *, the FAA 

published Special Federal Aviation 

Regulation (SFAR) 88 [(66 FR 23086, May 7, 

2001)], and the Joint Aviation Authorities 

(JAA) published Interim Policy INT/POL/25/ 

12. 

The review conducted by Fokker Services 

on the Fokker 27 design in response to these 

regulations revealed that no controlled 

bonding provisions are present on a number 

of critical locations outside the fuel tanks. 

This condition, if not corrected, could 

create an ignition source in the fuel tank 

vapour space, possibly resulting in a fuel 

tank explosion and consequent loss of the 

aeroplane. 

To address this potential unsafe condition, 

Fokker Services developed a set of bonding 

modifications, introduced with [a service 

bulletin] * * *, that do[es] not require 

opening of the fuel tank access panels. 

More information on this subject can be 

found in Fokker Services All Operators 

Message AOF27.043#03. 

For the reasons described above, this 

[EASA] AD requires installation of additional 

bonding provisions that do not require 

opening of the fuel tank access panels. 

Required actions also include revising 

the maintenance or inspection program, 

as applicable, by incorporating fuel 

airworthiness limitation items and 

critical design configuration control 

limitations. You may examine the MCAI 

in the AD docket on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

3633. 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 (66 FR 

23086, May 7, 2001) requires certain 


tkelley on DSK3SPTVN1PROD with PROPOSALS