57740 Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) 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. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary by sending a request to us 

at the address listed under ADDRESSES. 

Include ‘‘AD Docket No. 2001–NE–12–

AD’’ in your request. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends 14 CFR part 39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Amendment 39–12761 (67 FR 

36803, May 28, 2002) and by adding a 

new airworthiness directive, 

Amendment 39–14319, to read as 

follows: 

2005–20–23 Rolls-Royce plc: Amendment 

39–14319. Docket No. 2001–NE–12–AD. 

Effective Date 

(a) This AD becomes effective November 8, 

2005. 

Affected ADs 

(b) This AD supersedes AD 2002–10–15. 

Applicability 

(c) This AD applies to Rolls-Royce plc (RR) 

RB211 Trent 875, 877, 884, 884B, 892, 892B, 

and 895 series turbofan engines with low 

pressure compressor (LPC) fan blade part 

numbers (P/Ns): FK 30838, FK30840, 

FK30842, FW12960, FW12961, FW12962, 

FW13175, FW18548, or FW23552. These 

engines are installed on, but not limited to, 

Boeing 777 series airplanes. 

Unsafe Condition 

(d) This AD results from the discovery of 

dry film lubricant (DFL) condition appearing 

worse than anticipated on fan blades fitted to 

disks previously run for a significant period. 

This AD also results from the need to update 

the list of engine models affected, and to 

update the list of fan blade part numbers 

affected. The actions specified in this AD are 

intended to prevent LPC fan blade loss, 

which could result in an uncontained engine 

failure and possible aircraft damage. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

(f) Apply an approved DFL to LPC fan 

blade roots as follows: 

(1) For LPC fan blades P/Ns FW13175, 

FW12960, FW12961, FW12962, FW18548, 

and FW23552 that have never been removed 

from the disk, apply DFL at the first removal 

from the disk or before 1,200 cycles-inservice (CIS), whichever occurs first. 

(2) For LPC fan blades P/Ns FW13175, 

FW12960, FW12961, FW12962, FW18548, 

and FW23552 that have been removed from 

the disk since entering service, apply DFL 

before accumulating 600 cycles-since-new 

(CSN) or before accumulating 600 cyclessince-last DFL application, or within 200 CIS 

from the effective date of this AD, whichever 

occurs later. 

(3) For LPC fan blades P/Ns FK30842, 

FK30840, and FK300838, apply DFL before 

accumulating 600 CSN or before 

accumulating 600 cycles-since-last DFL 

application, or within 100 CIS after July 2, 

2002 (effective date of superseded AD 2002–

10–15), whichever occurs first. 

(4) Thereafter, reapply DFL to LPC fan 

blade roots within 600 cycles-since-last DFL 

application. 

(5) Information on applying DFL to fan 

blade roots can be found in RR Alert Service 

Bulletin No. RB.211–72–AD347, Revision 6, 

dated April 22, 2004, or Revision 7, dated 

August 2, 2005. 

Alternative Methods of Compliance 

(g) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(h) Civil Aviation Authority Airworthiness 

Directive G–2004–0008, dated April 29, 2004, 

also addresses the subject of this AD. 

Issued in Burlington, Massachusetts, on 

September 27, 2005. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–19845 Filed 10–3–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20917; Directorate 

Identifier 2004–NM–85–AD; Amendment 39–

14312; AD 2005–20–18] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, –200B, –200F, –200C, 

–100B, –300, –100B SUD, –400, –400D, 

and –400F Series Airplanes; and Model 

747SR Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding two 

existing airworthiness directives (AD), 

which apply to certain Boeing transport 

category airplanes. One AD currently 

requires doing certain inspections to 

detect cracks and corrosion around the 

lower bearing of the actuator attach 

fittings of the inboard and outboard 

flaps; repairing if necessary; and either 

overhauling the fittings or replacing 

them, which ends certain repetitive 

inspections. The other AD currently 

requires certain other inspections to 

detect discrepancies of the actuator 

attach fittings of the flaps, and followon and corrective actions if necessary, 

which ends the repetitive inspections of 

the first AD. For certain airplanes, this 

AD requires new inspections for 

discrepancies of the actuator attach 

fittings of the flaps, and follow-on and 

corrective actions if necessary, which 

ends the repetitive inspections of both 

existing ADs. For all airplanes, this AD 

requires repetitive overhaul/ 

replacements of the actuator attach 

fittings of both the inboard and outboard 

flaps. This AD results from reports of 

cracks of the actuator attach fittings of 

the trailing edge flaps. We are issuing 

this AD to prevent cracking and other 

damage of the actuator attach fittings of 

the trailing edge flaps, which could 

result in abnormal operation or 

Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 57741 

retraction of a trailing edge flap, and 

possible loss of controllability of the 

airplane. 

DATES: This AD becomes effective 

November 8, 2005. 

On May 8, 2003 (68 FR 19937, April 

23, 2003), the Director of the Federal 

Register approved the incorporation by 

reference of Boeing Alert Service 

Bulletin 747–57A2316, dated December 

19, 2002. 

On August 3, 2001 (66 FR 34526, June 

29, 2001), the Director of the Federal 

Register approved the incorporation by 

reference of Boeing Service Bulletin 

747–57A2310, Revision 1, dated 

November 23, 1999; and Boeing Service 

Bulletin 747–57A2310, Revision 2, 

dated February 22, 2001. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., Nassif Building, room PL–401, 

Washington, DC. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Gary 

Oltman, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 917–6443; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2001–13–12, amendment 

39–12292 (66 FR 34526, June 29, 2001), 

and AD 2003–08–11, amendment 39–

13124 (68 FR 19937, April 23, 2003). AD 

2001–13–12 applies to certain Boeing 

Model 747 series airplanes. AD 2003–

08–11 applies to all Boeing Model 747–

100, –200B, –200F, –200C, –100B, –300, 

–100B SUD, –400, –400D, and –400F 

series airplanes; and Model 747SR 

series airplanes. That NPRM was 

published in the Federal Register on 

April 13, 2005 (70 FR 19345). That 

NPRM proposed to continue to require 

the existing requirements of ADs 2001–

13–12, and 2003–08–11. For certain 

airplanes, that NPRM also proposed to 

require new inspections for 

discrepancies of the actuator attach 

fittings of the flaps, and follow-on and 

corrective actions if necessary, which 

ends the repetitive inspections of both 

existing ADs. For all airplanes, that 

NPRM also proposed to require 

repetitive overhaul/replacements of the 

fittings of both the inboard and outboard 

flaps. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Request for Clarification 

One commenter, the airplane 

manufacturer, requests that paragraph 

(r) of the NPRM be revised to apply to 

‘‘fittings’’ instead of ‘‘airplanes.’’ The 

commenter states that some operators 

may have complied with paragraph 

(o)(2) of the NPRM for some fittings, but 

not others. The commenter also states 

that the proposed actions in paragraph 

(r) are not necessary if the proposed 

actions in paragraph (o)(2) have been 

done. The commenter also requests that 

paragraph (r) be revised to clarify this 

point. 

We partially agree. We agree with the 

commenter to refer to ‘‘fittings’’ rather 

than ‘‘airplanes’’ in paragraph (r) and 

have revised the final rule accordingly. 

However, we do not agree that 

paragraph (r) needs to be clarified 

regarding paragraph (o)(2). Although the 

actions specified in paragraph (o)(2) 

(refers to Parts 2 through 5 of the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–57A2316, 

dated December 19, 2002) are identical 

to those in paragraphs (r) and (s), the 

affected fittings and compliance times 

in those paragraphs are different. 

Paragraph (r) states, ‘‘For [fittings] on 

which * * * the inspections required 

by [paragraph] (m), (n), or (o)(1) of this 

AD are being done as of the effective 

date of this AD.’’ The actions specified 

in paragraphs (m), (n), and (o)(1) are 

done in accordance with Part 1 of the 

Accomplishment Instructions of the 

referenced service bulletin. Paragraph 

(r) does not apply to fittings on which 

the actions specified in paragraph (o)(2) 

(i.e., Parts 2 through 5) are being done. 

Operators doing the actions specified in 

paragraph (o)(2) instead of the actions 

specified in paragraph (o)(1), must 

continue to do those actions at the 

specified times in paragraph (o)(2). 

Operators doing the actions in 

paragraph (o)(1) of this AD as of the 

effective date of this AD, must do the 

requirements of paragraph (r). We have 

made no change to the final rule in this 

regard. 

The same commenter notes that 

paragraph (t) of the NPRM states, ‘‘at the 

applicable time specified in Figures 1 

and 2 of the service bulletin.’’ The 

commenter requests that the reference to 

Figure 2 in that paragraph be deleted, 

because Figure 2 does not specify 

compliance times. 

We agree and have revised paragraph 

(t) accordingly. 

Explanation of Editorial Changes 

Based on the comment above that 

fittings may be overhauled at different 

times, we have clarified the terminating 

action in paragraphs (j)(1) and (j)(2) of 

the NPRM. Overhauling an actuator 

attach fitting on an applicable flap 

constitutes terminating action for the 

repetitive inspection requirements for 

that fitting. The remaining fittings that 

are not being repetitively overhauled 

must be repetitively inspected. 

Therefore, we have revised paragraphs 

(j)(1) and (j)(2) of this AD accordingly. 

Paragraph (r) of the NPRM applies to 

fittings on which the repetitive 

borescopic, detailed, ‘‘or’’ ultrasonic (as 

applicable) inspections required by 

paragraph (m), (n), or (o)(1) of this AD 

are being done as of the effective date 

of this AD. Paragraph (m) of the NPRM 

proposed to require both borescopic and 

detailed inspections. Paragraph (n) of 

the NPRM proposed to require 

borescopic, detailed, and ultrasonic 

inspections. Paragraph (o)(1) of the 

NPRM proposed to require applicable 

inspections specified in paragraphs (m) 

and (n). It was our intent that paragraph 

(r) apply to fittings on which the 

repetitive borescopic, detailed, ‘‘and’’

ultrasonic (as applicable) inspections 

required by paragraph (m), (n), or (o)(1) 

of this AD are being done as of the 

effective date of this AD. Therefore, we 

have revised paragraph (r) accordingly. 

Boeing Commercial Airplanes has 

received a Delegation Option 

Authorization (DOA). We have revised 

this AD to delegate the authority to 

approve an alternative method of 

compliance for any repair required by 

this AD to an Authorized Representative 

for the Boeing Commercial Airplanes 

DOA rather than a Designated 

Engineering Representative. 

Although paragraph (s) of the NPRM 

states, ‘‘except as provided by paragraph 

(u) of this AD,’’ paragraph (u) does not 

refer to paragraph (s). We have corrected 

this mistake in this AD. 

57742 Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 

Although paragraph (t) of the NPRM 

states, ‘‘except as provided by paragraph 

(v) of this AD,’’ paragraph (v) incorrectly 

refers to paragraph (s) rather than 

paragraph (t). In addition, paragraph (t) 

states, ‘‘If any discrepancy is detected 

during any inspection required by 

paragraph (r) * * *’’ The requirements 

of paragraph (t) also are required if any 

discrepancy is detected during an 

inspection required by paragraph (s), as 

specified in Boeing Alert Service 

Bulletin 747–57A2316, described in the 

preamble of the NPRM. We have 

corrected these mistakes in this AD. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have added a new paragraph (y)(2) 

and renumbered subsequent paragraphs 

to clarify the appropriate procedure for 

notifying the principal inspector before 

using any approved AMOC on any 

airplane to which the AMOC applies. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

This AD will affect about 1,000 Model 

747–100, –200B, –200F, –200C, –100B, 

–300, –100B SUD, –400, –400D, and 

–400F series airplanes; and Model 

747SR series airplanes worldwide. 

There are about 181 airplanes on the 

U.S. registry. The average labor rate is 

$65 per hour. The following two tables 

provide the estimated costs for U.S. 

operators to comply with this AD. 

TABLE 1.—ESTIMATED COSTS

Action Work 

hours Parts Cost per airplane Fleet cost 

Inspections (required by AD 2001–13–12) .......................................................... 2 None ........ $130, per inspection cycle.$23,530, per inspection cycle. 

Inspections specified in Part 1 of the Accomplishment Instruction (AI) of the 

referenced service bulletin (required by AD 2003–08–11).

2 None ........ $130 per inspection 

cycle.

$23,530 per inspection cycle. 

Inspections specified in Part 2 of the AI of the referenced service bulletin (new 

proposed actions).

5 None ........ $325 per inspection 

cycle.

$58,825 per inspection cycle. 

TABLE 2.—ESTIMATED COSTS

Action Work 

hours Parts Cost per airplane 

Overhaul(s) as an alternative to the replacement.37 None .......................................................................... $2,405. 

Replacement(s) as an alternative to the overhaul.4 $6,623 (for the four actuator attach fittings on the 

outboard flaps) and $7,566 (for the four actuator 

attach fittings on the inboard flaps).

$6,883 (for the four actuator attach fittings on the 

outboard flaps) and $7,826 (for the four actuator 

attach fittings on the inboard flaps), per replacement 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 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendments 39–12292 (66 

FR 34526, June 29, 2001) and 39–13124 

(68 FR 19937, April 23, 2003) and by 

adding the following new airworthiness 

directive (AD): 

Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 57743 

2005–20–18 Boeing: Amendment 39–14312. 

Docket No. FAA–2005–20917; 

Directorate Identifier 2004–NM–85–AD. 

Effective Date 

(a) This AD becomes effective November 8, 

2005. 

Affected ADs 

(b) This AD supersedes AD 2001–13–12, 

amendment 39–12292; and AD 2003–08–11, 

amendment 39–13124. 

Applicability 

(c) This AD applies to all Boeing Model 

747–100, –200B, –200F, –200C, –100B, –300, 

–100B SUD, –400, –400D, and –400F series 

airplanes; and Model 747SR series airplanes; 

certificated in any category. 

Unsafe Condition 

(d) This AD results from reports of cracks 

of the actuator attach fittings of the trailing 

edge flaps. We are issuing this AD to prevent 

cracking and other damage of the actuator 

attach fittings of the trailing edge flaps, 

which could result in abnormal operation or 

retraction of a trailing edge flap, and possible 

loss of controllability of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Requirements of AD 2001–13–12 

Affected Airplanes 

(f) For Boeing Model 747 series airplanes, 

as listed in Boeing Service Bulletin 747–

57A2310, Revision 2, dated February 22, 

2001, do the actions required by paragraphs 

(g) through (l) of this AD, as applicable. 

Actuator Attach Fittings That Have Not Been 

Overhauled or Replaced 

(g) For actuator attach fittings on the 

outboard flaps that have not been overhauled 

in accordance with revisions of Boeing 747 

Overhaul Manual (OHM) 57–52–55 dated 

prior to June 1, 1999, or replaced with a new 

fitting, prior to August 3, 2001 (the effective 

date of AD 2001–13–12); and for actuator 

attach fittings on the inboard flap actuators 

that have not been overhauled in accordance 

with revisions of OHM 57–52–35, dated prior 

to June 1, 1999, or replaced with a new 

fitting, prior to August 3, 2001: Accomplish 

the actions in paragraph (i), (j), or (k) of this 

AD at the later of the times specified in 

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

(1) Prior to the accumulation of 8 years 

since date of manufacture or 8,000 total flight 

cycles, whichever occurs first. 

(2) Within 6 months after August 3, 2001. 

Actuator Attach Fittings That Have Been 

Overhauled or Replaced 

(h) For actuator attach fittings on the 

outboard flaps that have been overhauled in 

accordance with revisions of OHM 57–52–55 

dated prior to June 1, 1999, or replaced with 

a new fitting, prior to August 3, 2001; and for 

actuator attach fittings on the inboard flap 

actuators that have been overhauled in 

accordance with revisions of OHM 57–52–35 

dated prior to June 1, 1999, or replaced with 

a new fitting, prior to August 3, 2001: 

Accomplish the actions in paragraph (i), (j), 

or (k) of this AD at the later of the times 

specified in paragraphs (h)(1) and (h)(2) of 

this AD. 

(1) Within 8 years or 8,000 total flight 

cycles after the attach fitting was overhauled 

or replaced, whichever occurs first. 

(2) Within 6 months after August 3, 2001. 

Inspections and Corrective Action 

(i) Perform a detailed inspection to detect 

corrosion around the lower bearing journal 

on the actuator attach fittings on the inboard 

and outboard flaps, and perform an 

ultrasonic inspection to detect cracks around 

the lower bearing journal of the actuator 

attach fittings on the outboard flaps, in 

accordance with Boeing Service Bulletin 

747–57A2310, Revision 1, dated November 

23, 1999; or Revision 2, dated February 22, 

2001. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Note 2: Inspections, overhauls, and 

replacements accomplished in accordance 

with Boeing Alert Service Bulletin 747–

57A2310, dated June 17, 1999, are acceptable 

for compliance with the requirements of 

paragraph (i) of this AD. 

(1) If no corrosion or cracks are detected, 

repeat the inspections required by paragraph 

(i) of this AD at intervals not to exceed 18 

months. Within 5 years after the initial 

inspections required by paragraph (i) of this 

AD, accomplish the actions specified in 

paragraph (j) or (k) of this AD. 

(2) If any corrosion is detected, prior to 

further flight, remove the corrosion by 

accomplishing the actions of either paragraph 

(i)(2)(i) or (i)(2)(ii) of this AD. 

(i) If corrosion is within the limits of the 

Boeing 747 OHM: Prior to further flight, 

accomplish the actions specified in 

paragraph (j) or (k) of this AD. 

(ii) If corrosion is not within the limits of 

the Boeing 747 OHM: Prior to further flight, 

accomplish the actions specified in 

paragraph (k) or (l) of this AD. 

(3) If any crack is detected: Prior to further 

flight, accomplish the actions specified in 

paragraph (k) or (l) of this AD. 

Overhaul 

(j) Do the actions as specified in paragraphs 

(j)(1) and (j)(2) of this AD in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin 747–57A2310, Revision 1, 

dated November 23, 1999; or Revision 2, 

dated February 22, 2001. 

(1) Overhaul the actuator attach fittings on 

the outboard flaps. Repeat the overhaul of the 

fittings on the outboard flaps as specified in 

Part 2 of the Work Instructions of the service 

bulletin thereafter at intervals not to exceed 

8 years or 8,000 flight cycles, whichever 

occurs first. As of the effective date of this 

AD, the repetitive overhauls must be done in 

accordance with Part 5 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2316, dated 

December 19, 2002, at intervals not to exceed 

8 years since last overhaul. Overhauling an 

actuator attach fitting on an outboard flap 

constitutes terminating action for the 

repetitive inspection requirements of 

paragraph (i)(1) of this AD for that fitting. 

(2) Overhaul the actuator attach fittings on 

the inboard flaps. Overhauling an actuator 

attach fitting on an inboard flap constitutes 

terminating action for the requirements of 

paragraphs (g) through (l) of this AD for that 

fitting. 

Replacement 

(k) Replace the actuator attach fittings on 

the inboard and outboard flaps in accordance 

with paragraph (k)(1) or (k)(2) of this AD. 

(1) Replace the actuator attach fittings on 

the inboard and outboard flaps with new 

actuator attach fittings in accordance with 

‘‘Part 3—Replacement’’ of Boeing Service 

Bulletin 747–57A2310, Revision 1, dated 

November 23, 1999; or Revision 2, dated 

February 22, 2001. Accomplishment of this 

replacement constitutes terminating action 

for the repetitive inspections required by 

paragraph (i) of this AD for the replaced 

fitting. Within 8 years or 8,000 flight cycles 

following accomplishment of the 

replacement, whichever occurs first, repeat 

this replacement or accomplish the overhaul 

specified in paragraph (j) of this AD. As of 

the effective date of this AD, the repetitive 

replacements must be done in accordance 

with Part 5 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2316, dated December 19, 2002, at 

intervals not to exceed 8 years since last 

replacement. 

(2) Replace the actuator attach fittings on 

the inboard and outboard flaps with 

improved actuator attach fittings in 

accordance with ‘‘Part 4—Terminating 

Action’’ of Boeing Service Bulletin 747–

57A2310, Revision 2, dated February 22, 

2001. If accomplished, this replacement with 

improved fittings terminates the 

requirements of paragraphs (g) through (l) of 

this AD for the replaced fitting. 

Note 3: Replacement of the actuator attach 

fittings on the inboard flaps with fittings that 

have been overhauled before the effective 

date of this AD, in accordance with Boeing 

OHM 57–52–35, Temporary Revision 57–8, 

dated June 10, 1999; Temporary Revision 57–

10, dated May 8, 2000; or Full Revision 57–

10, dated July 1, 2000; constitutes 

terminating action for the requirements of 

paragraphs (g) through (l) of this AD for the 

actuator attach fittings on the inboard flaps. 

Repair 

(l) During any inspection done in 

accordance with paragraph (i) of this AD, if 

corrosion is found that is outside the limits 

specified in the Boeing 747 OHM, or if any 

crack is detected: In lieu of replacement of 

the actuator attach fittings in accordance 

with paragraph (k) of this AD, repair the 

actuator attach fittings on the inboard and 

outboard flaps in accordance with a method 

57744 Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 

approved by the Manager, Seattle Aircraft 

Certification Office (ACO), FAA; or using a 

method approved in accordance with 

paragraph (y)(3) of this AD. 

Requirements of AD 2003–08–11 

Inspection: Inboard Flap Actuator Attach 

Fittings 

(m) Perform borescopic and detailed 

inspections to detect discrepancies of the 

actuator attach fittings of the inboard flap , 

in accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2316, dated 

December 19, 2002. Discrepancies include 

corrosion, pitting, and damaged or missing 

cadmium plating. Do the inspection at the 

applicable time specified in paragraph (m)(1) 

or (m)(2) of this AD. 

(1) If the age of the fittings can be 

determined: Inspect within 14 years since the 

fittings were new or last overhauled, or 

within 90 days after May 8, 2003 (the 

effective date of AD 2003–08–11), whichever 

occurs later. 

(2) If the age of the fittings cannot be 

determined: Inspect within 90 days after May 

8, 2003. 

Note 4: The exceptions specified in flag 

note 4 of Figure 1 of Boeing Alert Service 

Bulletin 747–57A2316, dated December 19, 

2002, apply to the requirements of 

paragraphs (m) and (n) of this AD. 

Inspection: Outboard Flap Actuator Attach 

Fittings 

(n) Perform borescopic, detailed, and 

ultrasonic inspections to detect discrepancies 

of the actuator attach fittings of the outboard 

flap , in accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2316, dated 

December 19, 2002. Discrepancies include 

surface corrosion, pitting, damaged or 

missing cadmium plating, and cracks. Do the 

inspection at the applicable time specified in 

paragraph (n)(1) or (n)(2) of this AD. 

(1) If the age of the fittings can be 

determined: Inspect within 8 years since the 

fittings were new or last overhauled, or 

within 90 days after May 8, 2003, whichever 

occurs later. 

(2) If the age of the fittings cannot be 

determined: Inspect within 90 days after May 

8, 2003. 

Follow-on Actions: No Discrepancies Found 

(o) If no discrepancy is found during any 

inspection required by paragraph (m) through 

(p) of this AD: Do the actions specified by 

either paragraph (o)(1) or paragraph (o)(2) of 

this AD. 

(1) Repeat the applicable inspections 

specified in paragraphs (m) and (n) of this 

AD at intervals not to exceed 9 months until 

the actions specified in paragraph (o)(2) of 

this AD have been accomplished. 

(2) Perform a detailed inspection of the 

fitting to detect cracks, corrosion, damaged 

cadmium plating, or bushing migration, in 

accordance with and at the time specified in 

Part 2 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2316, 

dated December 19, 2002. Do the follow-on 

actions in accordance with Parts 3, 4, and 5 

of the Accomplishment Instructions of the 

service bulletin at the times specified in 

Figure 1 of the service bulletin, as applicable. 

Accomplishment of these actions terminates 

the initial and repetitive inspection 

requirements of paragraphs (m), (n), and 

(o)(1) of this AD. 

Note 5: The exceptions specified in flag 

note 2 of Figure 1 of Boeing Alert Service 

Bulletin 747–57A2316, dated December 19, 

2002, apply to those requirements of 

paragraphs (o)(2) and (p) of this AD that are 

specified in Part 2 of the service bulletin. 

Corrective/Follow-on Actions: Discrepancies 

Found 

(p) If any discrepancy is found during any 

inspection required by paragraph (m), (n), or 

(o) of this AD: Perform applicable corrective 

and follow-on actions at the time specified 

and in accordance with Figure 1 of Boeing 

Alert Service Bulletin 747–57A2316, dated 

December 19, 2002. Before further flight: 

Replace any discrepant fitting in accordance 

with Part 5 of the Accomplishment 

Instructions of the service bulletin, and 

accomplish the follow-on actions for the 

other fittings common to that flap in 

accordance with Part 2 of the 

Accomplishment Instructions of the service 

bulletin. Replacement of a fitting terminates 

the initial and repetitive inspections—

specified in paragraphs (m), (n), and (o) of 

this AD—for that fitting only. 

Terminating Action for Certain Requirements 

(q) Accomplishment of the actions required 

by paragraphs (m) and (n) of this AD ends the 

requirements of paragraphs (g) through (k) of 

this AD, except for the repetitive overhauls 

and repetitive replacements required by 

paragraphs (j)(1) and (k)(1) of this AD, 

respectively. 

New Actions Required by This AD 

Inspections: Actuator Attach Fittings of the 

Inboard and Outboard Flaps 

(r) For fittings on which the repetitive 

borescopic, detailed, and ultrasonic (as 

applicable) inspections required by 

paragraph (m), (n), or (o)(1) of this AD are 

being done as of the effective date of this AD: 

Inspect as specified in Table 1 of this AD. 

Accomplishing these actions ends the initial 

and repetitive inspections required by 

paragraphs (m), (n), and (o)(1) of this AD. 

TABLE 1.—INSPECTIONS OF ACTUATOR ATTACH FITTINGS

Requirements Description 

(1) Compliance time: Except as provided by paragraph (u) of this AD, at the applicable time specified in Figure 1 of 

Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002. 

(2) Area to inspect: The actuator attach fittings of the inboard and outboard flaps. 

(3) Type of inspection: Detailed inspection (inboard and outboard flaps) and ultrasonic inspection (outboard flaps 

only). 

(4) Discrepancies to detect: Surface corrosion, pitting, cracks, migrated or rotated bushings, and damaged or missing cadmium plating. 

(5) In accordance with: Part 2 of the Work Instructions of Boeing Alert Service Bulletin 747–57A2316, dated December 19, 2002. 

Follow-on Actions: No Discrepancies 

Detected 

(s) If no discrepancy is detected during any 

inspection required by paragraph (r) of this 

AD: Do the follow-on actions in accordance 

with Parts 3, 4, and 5, as applicable, of the 

Work Instructions of Boeing Alert Service 

Bulletin 747–57A2316, dated December 19, 

2002, at the applicable times specified in 

Figure 1 of the service bulletin, except as 

provided by paragraph (u) of this AD. 

Overhaul/Replacement and Follow-on/ 

Corrective Actions: Discrepancies Detected 

(t) If any discrepancy is detected during 

any inspection required by paragraph (r) or 

(s) of this AD: Do the actions specified in 

Table 2 of this AD at the applicable times 

specified in Figure 1 of the service bulletin, 

except as provided by paragraph (v) of this 

AD. 

Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 57745 

TABLE 2.—DISCREPANCIES FOUND

Requirements In accordance with Boeing Alert Service Bulletin 747–57A2316, dated 

December 19, 2002—

(1) Overhaul or replace discrepant fitting with new fitting ....................... Part 5 of Work Instructions. 

(2) Do the follow-on and corrective actions for the other fitting common 

to that flap, except as specified in flag note 2 in Figure 1 of the service bulletin.

Parts 2 and 5 of Work Instructions, as applicable. 

Compliance Time Requirements 

(u) For the requirements of paragraphs (r) 

and (s) of this AD: Where Figure 1 of Boeing 

Alert Service Bulletin 747–57A2316, dated 

December 19, 2002, states a compliance time 

‘‘after the original issue date of the service 

bulletin,’’ this AD requires compliance 

within the applicable compliance time after 

the effective date of this AD. 

(v) For the requirements of paragraph (t) of 

this AD: Where Figure 1 of Boeing Alert 

Service Bulletin 747–57A2316, dated 

December 19, 2002, specifies to repeat the 

overhaul or replacement ‘‘every 8 years,’’ this 

AD requires compliance at intervals not to 

exceed 8 years. 

Repetitive Overhaul or Replacement 

(w) Except as provided in paragraph (x) of 

this AD, at the applicable time specified in 

paragraph (w)(1) or (w)(2) of this AD, 

overhaul the actuator attach fittings on the 

outboard and inboard flaps or replace the 

actuator attach fittings with new or 

overhauled fittings, in accordance with Part 

5 of the Work Instructions of Boeing Alert 

Service Bulletin 747–57A2316, dated 

December 19, 2002. Repeat the overhaul or 

replacement thereafter at intervals not to 

exceed 8 years. 

(1) If the age of the fittings can be 

determined: Overhaul or replace within 8 

years since the fittings were new or last 

overhauled, or within 2 years after the 

effective date of this AD, whichever occurs 

later. 

(2) If the age of the fittings cannot be 

determined: Assume that the fittings are 

more than 14 years old, and overhaul or 

replace within 2 years after the effective date 

of this AD. 

(x) Accomplishing the repetitive overhauls 

required by paragraph (j)(1) or repetitive 

replacements required by paragraph (k)(1) of 

this AD is acceptable for compliance with the 

requirements of paragraph (w) of this AD. 

Alternative Methods of Compliance (AMOCs) 

(y)(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested in accordance with the 

procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards 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 an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2001–13–12 are 

approved as AMOCs with the actions 

required by paragraphs (g) through (l) of this 

AD, as applicable. However, AMOCs 

approved previously are not considered 

terminating action for the repetitive 

overhauls or replacements requirements of 

this AD. 

(5) AMOCs approved previously in 

accordance with AD 2003–08–11 are 

approved as AMOCs with the actions 

required by paragraphs (m) through (p) of 

this AD, as applicable. 

Material Incorporated by Reference 

(z) You must use the service bulletin in 

Table 3 of this AD to perform the actions that 

are required by this AD, unless the AD 

specifies otherwise. 

(1) On May 8, 2003 (68 FR 19937, April 23, 

2003), the Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 747–57A2316, 

dated December 19, 2002. 

(2) On August 3, 2001 (66 FR 34526, June 

29, 2001), the Director of the Federal Register 

approved the incorporation by reference of 

Boeing Service Bulletin 747–57A2310, 

Revision 1, dated November 23, 1999; and 

Boeing Service Bulletin 747–57A2310, 

Revision 2, dated February 22, 2001. 

(3) Contact Boeing Commercial Airplanes, 

Long Beach Division, 3855 Lakewood 

Boulevard, Long Beach, California 90846, 

Attention: Data and Service Management, 

Dept. C1–L5A (D800–0024), for a copy of this 

service information. You may review copies 

at the Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street SW., room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

TABLE 3.—MATERIAL INCORPORATED BY REFERENCE

Service bulletin Revision 

level Date 

Boeing Alert Service Bulletin 747–57A2316 .............................................................................................. Original December 19, 2002. 

Boeing Service Bulletin 747–57A2310 ....................................................................................................... 1 November 23, 1999. 

Boeing Service Bulletin 747–57A2310 ....................................................................................................... 2 February 22, 2001. 

57746 Federal Register / Vol. 70, No. 191 / Tuesday, October 4, 2005 / Rules and Regulations 

Issued in Renton, Washington, on 

September 26, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19876 Filed 10–3–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2005–21166; Airspace 

Docket No. 05–AWP–4] 

Establishment of Class E Airspace; 

Hana, HI 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action establishes a Class 

E airspace area at Hana, HI. The 

establishment of an Area Navigation 

(RNAV) Global Positioning System 

(GPS) Instrument Approach Procedures 

(IAP) RNAV (GPS) to Runway (RWY) 26 

IAP and a RNAV Departure Procedure 

(DP) at Hana Airport, Hana, HI has made 

this action necessary. Additional 

controlled airspace extending upward 

from 700 feet or more above the surface 

of the earth is needed to contain aircraft 

executing this RNAV (GPS) IAP and 

RNAV DP. The intended effect of this 

action is to provide adequate controlled 

airspace for Instrument Flight Rules 

operations at Hana Airport, Hana, HI. 

DATES: Effective 0901 UTC October 27, 

2005. 

FOR FURTHER INFORMATION CONTACT: 

Debra Trindle, The Office of the 

Regional Western Terminal Operations, 

Federal Aviation Administration, at 

15000 Aviation Boulevard, Lawndale, 

California 90261, telephone (310) 725–

6613. 

SUPPLEMENTARY INFORMATION: 

History 

On August 3, 2005, the FAA proposed 

to amend 14 CFR parts 71 by modifying 

the Class E airspace area at Hana 

Airport, HI (05 FR 15314). Additional 

controlled airspace extending upward 

from 700 feet or more above the surface 

is needed to contain aircraft executing 

the RNAV (GPS) (RWY) 26 IAP and 

RNAV DP at Hana Airport, Hana, HI. 

This action will provide adequate 

controlled airspace for aircraft executing 

the RNAV (GPS) (RWY) 26 IAP and 

RNAV DP at Hana Airport, Hana, HI. 

Interested parties were invited to 

participate in this rulemaking, 

proceeding by submitting written 

comments on the proposal to the FAA. 

No comments to the proposal were 

received. Class E airspace designations 

for airspace extending from 700 feet or 

more above the surface of the earth are 

published in paragraph 6005 of FAA 

Order 7400.9N, dated August September 

1, 2005, and effective September 16, 

2005, which is incorporated by 

reference in 14 CFR 71.1. The Class E 

airspace designation listed in this 

document will be published 

subsequently in the Order. 

The Rule 

This amendment to 14 CFR part 71 

modifies the Class E airspace area at 

Hana Airport, HI. The establishment of 

a RNAV (GPS) (RWY) 26 IAP and RNAV 

DP at Hana Airport has made this action 

necessary. The effect of this action will 

provide adequate airspace for aircraft 

executing the RNAV (GPS) (RWY) 26 

IAP and RNAV DP at Hana Airport, 

Hana, HI. 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. Therefore, this regulation—(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); and (3) 

does not warrant preparation of a 

Regulatory Evaluation as the anticipated 

impact is so minimal. Since this is a 

routine matter that will only affect air 

traffic procedures and air navigation, it 

is certified that this rule will not have 

a significant economic impact on a 

substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 71 

Airspace, Incorporation by reference, 

Navigation (air). 

Adoption of the Amendment 

■ In consideration of the foregoing, the 

Federal Aviation Administration 

amends 14 CFR part 71 as follows: 

PART 71—DESIGNATION OF CLASS A, 

CLASS B, CLASS C, CLASS D, AND 

CLASS E AIRSPACE AREAS; ROUTES; 

AND REPORTING POINTS. 

■ 1. The authority citation for 14 CFR 

part 71 continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40103, 40113, 

40120; E.O. 10854, 24 FR 9565, 3 CFR, 1959–

1963 Comp., p. 389; 14 CFR 11.69. 

§ 71.1 [Amended] 

■ 2. The incorporation by reference in 

14 CFR 71.1 of the Federal Aviation 

Administration Order 7400.9N, 

Airspace Designations and Reporting 

Points, dated September 1, 2005, and 

effective September 16, 2005, is 

amended as follows: 

Paragraph 6005 Class E airspace areas 

extending upward from 700 feet or more 

above the surface of the earth. 

* * * * * 

AWP HI E5 Hana, HI [New] 

Hana, HI 

(Lat. 20°47′44′′ N, long. 156°00′52′′ W) 

That airspace extending upward from 700 

feet above the surface within a 6.3-mile 

radius of the Hana Airport. 

* * * * * 

Dated: Issued in Los Angeles, California, 

on September 21, 2005. 

Leonard Mobley, 

Acting Area Director, Western Terminal 

Operations. 

[FR Doc. 05–19855 Filed 10–3–05; 8:45am] 

BILLING CODE 4910–13–M 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30458; Amdt. No. 3135] 

Standard Instrument Approach 

Procedures; Miscellaneous 

Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This amendment amends 

Standard Instrument Approach 

Procedures (SIAPs) for operations at 

certain airports. These regulatory 

actions are needed because of changes 

occurring in the National Airspace 

System, such as the commissioning of 

new navigational facilities, addition of 

new obstacles, or changes in air traffic 

requirements. These changes are 

designed to provide safe and efficient 

use of the navigable airspace and to 

promote safe flight operations under 

instrument flight rules at the affected 

airports. 

DATES: This rule is effective October 4, 

2005. The compliance date for each 

SIAP is specified in the amendatory 

provisions. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director