5066 Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules 

Issued in Renton, Washington, on January 

21, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–1793 Filed 1–31–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20243; Directorate 

Identifier 2004–NM–153–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747 Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Boeing Model 747–100, –200, –300, and 

747SP series airplanes. The existing AD 

currently requires certain inspections to 

find missing or alloy-steel taperlock 

fasteners (bolts) in the diagonal brace 

underwing fittings, and corrective 

actions if necessary. For airplanes with 

missing or alloy-steel fasteners, the 

existing AD also mandates replacement 

of certain fasteners with new fasteners, 

which constitutes terminating action for 

certain inspections. This proposed AD 

would expand the applicability to 

include additional airplane models and 

would require a new inspection to 

determine fastener material and to find 

missing or broken fasteners, and related 

investigative/corrective actions if 

necessary. This proposed AD is 

prompted by reports indicating that 

cracked fasteners made of A286 material 

were found on airplanes that had only 

fasteners made of A286 material 

installed in the area common to the 

diagonal brace underwing fittings. We 

are proposing this AD to prevent loss of 

the underwing fitting load path due to 

missing or damaged alloy-steel or A286 

taperlock fasteners, which could result 

in separation of the engine and strut 

from the airplane.

DATES: We must receive comments on 

this proposed AD by March 18, 2005.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web Site: Go to

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide Rulemaking Web 

Site: Go to http://www.regulations.gov

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., 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 Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

You can examine the contents of this 

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., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC. 

This docket number is FAA–2005–

20243; the directorate identifier for this 

docket is 2004–NM–153–AD.

FOR FURTHER INFORMATION CONTACT:

Nicholas Kusz, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6432; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2005–20243; Directorate Identifier 

2004–NM–153–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http://

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of our docket 

Web site, anyone can find and read the 

comments in any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). You can 

review the DOT’s complete Privacy Act 

Statement in the Federal Register

published on April 11, 2000 (65 FR 

19477–78), or you can visit http://

dms.dot.gov.

Examining the Docket 

You can examine the 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 DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them. 

Discussion 

On June 19, 2001, we issued AD 

2001–13–06, amendment 39–12286 (66 

FR 34094, June 27, 2001), for certain 

Boeing Model 747–100, –200, –300, and 

747SP series airplanes. That AD 

requires certain inspections to find 

missing or alloy-steel taperlock fasteners 

(bolts) in the diagonal brace underwing 

fittings; and corrective actions, if 

necessary. For airplanes with missing or 

alloy-steel fasteners, that AD also 

mandates replacement of certain 

fasteners with new fasteners, which 

constitutes terminating action for the 

repetitive inspection. That AD was 

prompted by a report indicating that 

broken taperlock fasteners (bolts) were 

found on the diagonal brace underwing 

fittings on the outboard strut at the 

Number 1 and Number 4 engine pylons 

on a Boeing Model 747–200 series 

airplane having titanium underwing 

fittings. We issued that AD to prevent 

loss of the underwing fitting load path 

due to missing or damaged alloy-steel 

taperlock fasteners, which could result 

in separation of the engine and strut 

from the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2001–13–06, we 

have received reports indicating that 

fractured fasteners have been found on 

Model 747–200B series airplanes that 

weren’t included in the applicability of 

the existing AD. The fractured fasteners 

were made of A286 material, and only 

fasteners made of that material were 

installed in the diagonal brace 

underwing fitting. (After this, this 

proposed AD refers to fasteners made of 

A286 material as ‘‘A286 fasteners.’’) 

Previously, cracked or broken A286 

fasteners were found only on airplanes 

that had a combination of alloy-steel 

and A286 fasteners. Thus, these 

previous incidents were attributed to 

overload of the A286 fasteners due to 

Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules 5067

fracture of adjacent alloy-steel bolts. 

Fractured alloy-steel or A286 fasteners 

could lead to loss of the underwing 

fitting load path, which could result in 

separation of the engine and strut from 

the airplane.

Alloy-steel or A286 fasteners may be 

installed in the diagonal brace 

underwing fitting on certain 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. Therefore, all of these models 

and series may be subject to the unsafe 

condition revealed on the Boeing Model 

747–200B series airplanes. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 747–57A2312, Revision 

1, dated April 29, 2004. The service 

bulletin describes procedures for 

performing the following actions for the 

fasteners in the diagonal brace 

underwing fittings: 

• A general visual inspection to 

ensure that all fasteners are installed 

and unbroken. 

• A magnetic inspection to determine 

fastener material. 

• If any alloy-steel or A286 fastener is 

found, repetitive ultrasonic inspections 

for damage of all 10 aft fasteners 

(regardless of material). 

• Replacement of damaged fasteners 

with new, improved fasteners 

(including an open-hole eddy current 

inspection for cracking of the fastener 

holes, and repair if necessary). 

• Replacement of all alloy steel and 

A286 fasteners with new, improved 

fasteners (including an open-hole eddy 

current inspection for cracking of the 

fastener holes, and repair if necessary), 

which eliminates the need for the 

repetitive inspections. 

If any damage is found that exceeds 

certain limits, the service bulletin 

recommends contacting Boeing for 

appropriate action. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other products of this same 

type design. This proposed AD would 

supersede AD 2001–13–06. This 

proposed AD would retain the 

requirements of the existing AD. This 

proposed AD would also expand the 

applicability of the existing AD and 

require accomplishing the actions 

specified in the service bulletin 

described previously, except as 

discussed under ‘‘Differences Between 

the Proposed AD and Service Bulletin.’’

Differences Between the Proposed AD 

and Service Bulletin 

The service bulletin specifies a 

magnetic inspection to detect alloy-steel 

fasteners. We find that a detailed 

inspection is also necessary to detect 

A286 fasteners. For the purposes of this 

AD, an A286 fastener is any fastener to 

which the magnet is not attracted, and 

which cannot be conclusively 

determined to have a part number that 

begins with BACB30NX (fasteners of T1 

material) or BACB30US (fasteners of 

Inconel material). This difference has 

been coordinated with the airplane 

manufacturer, and it agrees with our 

determination. If Boeing Alert Service 

Bulletin 747–57A2312 is revised in the 

future, the new revision will take into 

account the proposed requirements of 

this AD. 

If any A286 fastener is found during 

the inspection to determine material 

type, the service bulletin specifies that 

you must do an ultrasonic inspection for 

damage of all 10 aft fasteners in the 

diagonal brace underwing fitting. 

However, this proposed AD would 

require you to perform an ultrasonic 

inspection for damage of only alloy-steel 

and A286 fasteners, unless a cracked (or 

otherwise damaged) fastener is found. If 

a cracked or otherwise damaged fastener 

is found, this proposed AD would 

require ultrasonic inspection for damage 

of all 10 aft fasteners. This difference 

has been coordinated with the airplane 

manufacturer, and it agrees with our 

determination. If Boeing Alert Service 

Bulletin 747–57A2312 is revised in the 

future, the new revision will take into 

account the proposed requirements of 

this AD. 

Figure 1 of the service bulletin 

recommends that you perform a general 

visual inspection to ensure that all 

fasteners are installed and unbroken. 

We have determined that the procedures 

needed for this inspection constitute a 

detailed inspection. Note 1 of this AD 

defines a detailed inspection. This 

difference has been coordinated with 

the airplane manufacturer, and it agrees 

with our determination. If Boeing Alert 

Service Bulletin 747–57A2312 is revised 

in the future, the new revision will take 

into account the proposed requirements 

of this AD. 

Section 1.E., Table 1, of the service 

bulletin specifies an initial inspection 

threshold of between 11,000 and 29,000 

total flight cycles for the inspection to 

detect A286 fasteners. Section 1.E. of 

the service bulletin also specifies a grace 

period of 18 months after the issue date 

of Revision 1 of the service bulletin. 

This proposed AD would require 

compliance prior to the threshold 

specified in the service bulletin, or 

within 18 months after the effective date 

of the AD, whichever occurs later. 

The service bulletin specifies that you 

may contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require you to repair those conditions in 

one of the following ways: 

• Using a method that the Manager of 

the Seattle Aircraft Certification Office 

approves; or 

• Using data that meet the 

certification basis of the airplane that 

have been approved by an Authorized 

Representative for the Boeing Delegation 

Option Authorization Organization who 

has been authorized by the FAA to make 

those findings. 

Changes to Existing AD 

This proposed AD would retain all 

requirements of AD 2001–13–06. Since 

AD 2001–13–06 was issued, the AD 

format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this 

proposed AD, as listed in the following 

table:

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2001–13–06 

Corresponding

requirement in this 

proposed AD 

Paragraph (a) ............ Paragraph (f). 

Paragraph (b) ............ Paragraph (g). 

Paragraph (c) ............ Paragraph (l). 

Paragraph (d) ............ Paragraph (n). 

Also, we have changed all references 

to a ‘‘detailed visual inspection’’ in the 

existing AD to ‘‘detailed inspection’’ in 

this action. Note 1 defines a ‘‘detailed 

inspection.’’

Costs of Compliance 

There are about 739 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD, at an 

average labor rate of $65 per work hour.

5068 Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules 

ESTIMATED COSTS

Action Work hours Parts Cost per

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Detailed and magnetic inspection (required by AD 

2001–13–06).

2 None ........................ $130 60 $7,800 

Detailed and magnetic inspections (new proposed 

action).

3 None ........................ 195 140 27,300 

Authority for This Rulemaking 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 

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. 

This rulemaking is promulgated 

under the authority described in subtitle 

VII, part A, subpart III, section 44701, 

‘‘General requirements.’’ Under that 

section, the FAA is charged 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 AD. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 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 proposed AD. 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, 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 

removing amendment 39–12286 (66 FR 

34094, June 27, 2001) and adding the 

following new airworthiness directive 

(AD):

Boeing: Docket No. FAA–2005–20243; 

Directorate Identifier 2004–NM–153–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this airworthiness 

directive (AD) action by March 18, 2005. 

Affected ADs 

(b) This AD supersedes AD 2001–13–06, 

amendment 39–12286 (66 FR 34094, June 27, 

2001). 

Applicability: 

(c) This AD applies to Model 747–100, 

747–100B, 747–100B SUD, –200B, 747–200C, 

747–200F, 747–300, 747 –400, 747–400D, 

747–400F, 747SR, and 747SP series 

airplanes; certificated in any category; as 

identified in Boeing Alert Service Bulletin 

747–57A2312, Revision 1, dated April 29, 

2004. 

Unsafe Condition 

(d) This AD was prompted by reports 

indicating that cracked fasteners made of 

A286 material were found on airplanes that 

had only fasteners made of A286 material 

installed in the area common to the diagonal 

brace underwing fittings. We are issuing this 

AD to prevent loss of the underwing fitting 

load path due to missing or damaged alloysteel or A286 taperlock fasteners, which 

could result in separation of the engine and 

strut from 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 2001–13–06: 

Repetitive Inspections 

(f) For Boeing Model 747–100, 747–200, 

747–300, and 747SP series airplanes 

equipped with titanium diagonal brace 

underwing fittings, as identified in Boeing 

Alert Service Bulletin 747–57A2312, dated 

June 15, 2000: Within 12 months after August 

1, 2001 (the effective date of AD 2001–13–06, 

amendment 39–12286), do a one-time 

detailed inspection of the diagonal brace 

underwing fitting at the Number 1 and 

Number 4 engine pylons to find missing 

taperlock fasteners (bolts), and a magnetic 

inspection to find alloy-steel fasteners per 

Part 1 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2312, 

dated June 15, 2000, or Revision 1, dated 

April 29, 2004.

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.’’

(1) If no alloy-steel fasteners are found and 

no fasteners are missing, no further action is 

required by this paragraph. 

(2) If any alloy-steel fasteners are found or 

any fasteners are missing, before further 

flight, do an ultrasonic inspection of the 

alloy-steel fasteners to find damage per Part 

2 of the Accomplishment Instructions of the 

service bulletin. 

(i) If no damaged alloy-steel fasteners are 

found, and no fasteners are missing: Repeat 

the ultrasonic inspection thereafter at 

intervals not to exceed 18 months until 

accomplishment of the terminating action 

required by paragraph (g) of this AD. 

(ii) If any damaged alloy-steel fasteners are 

found, or any fasteners are missing: Before 

further flight, do an ultrasonic inspection of 

all 10 aft fasteners (including non-alloy steel) 

per Part 2 of the Accomplishment 

Instructions of the service bulletin. Before 

further flight, replace damaged and missing 

fasteners with new fasteners per Part 3 of the 

Accomplishment Instructions of the service 

bulletin, except as provided by paragraph (l) 

of this AD. Thereafter, repeat the inspection 

of the remaining alloy-steel fasteners at 

intervals not to exceed 18 months until 

accomplishment of the terminating action 

required by paragraph (g) or the optional 

terminating action specified in paragraph (m) 

of this AD. 

Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules 5069

Terminating Action 

(g) For Boeing Model 747–100, 747–200, 

747–300, and 747SP series airplanes 

equipped with titanium diagonal brace 

underwing fittings, as identified in Boeing 

Alert Service Bulletin 747–57A2312, dated 

June 15, 2000: Within 48 months after August 

1, 2001, do the actions required by 

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

AD, per Boeing Alert Service Bulletin 747–

57A2312, dated June 15, 2000, or Revision 1, 

dated April 29, 2004. Accomplishment of the 

actions specified in this paragraph 

constitutes terminating action for the 

repetitive inspection requirements of this 

AD.

(1) Perform an open-hole high frequency 

eddy current (HFEC) inspection to detect 

cracks, corrosion, or damage at the bolt hole 

locations of the aft 10 taperlock fasteners in 

the diagonal brace underwing fitting at the 

Number 1 and Number 4 engine pylons per 

Part 3 of the Accomplishment Instructions of 

the service bulletin. If any cracking is 

detected, before further flight, perform 

applicable corrective actions per the service 

bulletin, except as provided by paragraph (l) 

of this AD. 

(2) Before further flight: Replace all 10 aft 

taperlock fasteners with new, improved 

fasteners per Part 3 of the Accomplishment 

Instructions of the service bulletin. 

(3) Do an ultrasonic inspection to find 

damaged fasteners per Part 2 of the 

Accomplishment Instructions of the service 

bulletin. Before further flight, replace all 

damaged non-alloy steel and all alloy-steel 

fasteners with new fasteners per Part 3 of the 

Accomplishment Instructions of the service 

bulletin. Do an open-hole HFEC inspection 

before installation of the new fasteners; if any 

cracking, corrosion, or damage is found, 

before further flight, perform applicable 

corrective actions per the service bulletin, 

except as provided by paragraph (l) of this 

AD. 

New Requirements of This AD: 

Inspection for Missing/Broken Fasteners and 

To Determine Material Type 

(h) For all fasteners in the diagonal brace 

underwing fitting at the Number 1 and 

Number 4 engine pylons: Perform the 

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

this AD, as applicable. 

(1) For airplanes not identified in 

paragraph (f) of this AD: Within 12 months 

after the effective date of this AD, perform a 

detailed inspection to ensure that all 

fasteners are installed and unbroken, and a 

magnetic inspection to detect alloy-steel 

fasteners, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2312, Revision 1, 

dated April 29, 2004. 

(2) For all airplanes: Before the initial 

inspection threshold specified in Section 

1.E., Table 1, of Boeing Alert Service Bulletin 

747–57A2312, Revision 1, dated April 29, 

2004; or within 18 months after the effective 

date of this AD; whichever is later; perform 

detailed and magnetic inspections, as 

applicable, to detect A286 fasteners in the 

diagonal brace underwing fitting at the 

Number 1 and Number 4 engine pylons, as 

specified in Part 1 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2312, Revision 1, dated April 29, 

2004. For the purposes of this AD, an A286 

fastener is any fastener to which the magnet 

is not attracted, and which cannot be 

conclusively determined to be BACB30NX 

(T1 material) or BACB30US (Inconel 

material) fasteners. 

Ultrasonic Inspection for Damage 

(i) For all alloy-steel or A286 fasteners 

identified during the inspections in 

accordance with paragraph (h) of this AD: 

Before further flight, perform an ultrasonic 

inspection for damage (including, but not 

limited to, cracking or corrosion) of each 

alloy-steel and A286 fastener, in accordance 

with Part 2 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2312, Revision 1, dated April 29, 

2004. If any bolt is missing or found damaged 

during the inspection required by this 

paragraph: before further flight, perform an 

ultrasonic inspection for damage of all 10 

subject fasteners, in accordance with Part 2 

of the Accomplishment Instructions of the 

service bulletin. Doing the actions required 

by this paragraph within the compliance time 

specified in paragraph (f) of this AD 

eliminates the need to do paragraph (f) of this 

AD. 

Undamaged Fastener: Repetitive Inspections 

or No Further Action 

(j) For any fastener that is found to be 

installed and undamaged during the 

inspections required by paragraph (i) of this 

AD, do paragraph (j)(1), (j)(2), or (j)(3) of this 

AD, as applicable. 

(1) If no damage is found during the 

inspections required by paragraph (i) of this 

AD, and all 10 fasteners in the diagonal brace 

underwing fitting at the Number 1 and 

Number 4 engine pylons are either 

BACB30NX or BACB30US fasteners: No 

further action is required by this AD, though 

the restrictions of paragraph (n) of this AD, 

‘‘Parts Installation,’’ apply. 

(2) For any undamaged alloy steel fastener: 

Repeat the ultrasonic inspection specified in 

paragraph (i) of this AD at intervals not to 

exceed 18 months, until the actions in 

paragraph (m) of this AD are done. 

(3) For any undamaged A286 fastener: 

Repeat the ultrasonic inspection specified in 

paragraph (i) of this AD at intervals not to 

exceed 8,000 flight cycles, until the actions 

in paragraph (m) of this AD are done. 

Repetitive Ultrasonic Inspections and 

Corrective Actions 

(k) For any missing or damaged fastener 

found during the inspections required by 

paragraph (i) or (j) of this AD: Before further 

flight, install a new, improved fastener in any 

location where a fastener is missing, and 

replace any damaged fastener with a new, 

improved fastener, in accordance with Part 3 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2312, 

Revision 1, dated April 29, 2004. Do an openhole HFEC inspection for cracking, corrosion, 

or damage before installing the new fastener. 

If any cracking, corrosion, or damage is 

found: Before further flight, perform 

applicable corrective actions in accordance 

with the service bulletin, except as provided 

by paragraph (l) of this AD. 

Repair 

(l) If any damage (including but not limited 

to cracking or corrosion) of the bolt hole that 

exceeds the limits specified in Boeing Alert 

Service Bulletin 747–57A2312, Revision 1, 

dated April 29, 2004, is found during any 

inspection required by this AD, and the 

service bulletin specifies to contact Boeing 

for appropriate action: Before further flight, 

repair per a method approved by the 

Manager, Seattle ACO, or according to data 

meeting the certification basis of the airplane 

approved by an Authorized Representative 

for the Boeing Delegation Option 

Authorization Organization who the 

Manager, Seattle ACO, has authorized to 

make this finding. For a repair method to be 

approved by the Manager, Seattle ACO, as 

required by this paragraph, the Manager’s 

approval letter must specifically reference 

this AD. 

Optional Terminating Action 

(m) Replacement of all alloy steel and 

A286 fasteners with new, improved fasteners 

in accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2312, Revision 1, 

dated April 29, 2004 (including performing 

an open-hole eddy current inspection for 

cracking of the fastener holes and repairing, 

as applicable), constitutes terminating action 

for the repetitive inspection requirements of 

this AD. 

Parts Installation 

(n) For Boeing Model 747–100, 747–200, 

747–300, and 747SP series airplanes 

equipped with titanium diagonal brace 

underwing fittings, as identified in Boeing 

Alert Service Bulletin 747–57A2312, dated 

June 15, 2000: As of August 1, 2001, no 

person may install, on any airplane, a 

fastener having part number 

BACB30PE( ) * ( ); or any other fastener made 

of 4340, 8740, PH13–8 Mo, or H–11 steel; in 

the locations specified in this AD. 

(o) Except as provided by paragraph (n) of 

this AD, as of the effective date of this AD 

no person may install, on any airplane, a 

fastener having part number 

BACB30PE( ) * ( ); or any other fastener made 

of 4340, 8740, PH13–8 Mo, A286, or H–11 

steel; in the locations specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(p)(1) The Manager, Seattle ACO, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) 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 

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. 

(3) AMOCs approved previously according 

to AD 2001–13–06, amendment 39–12286 (66 

5070 Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules 

FR 34094, June 27, 2001), are approved as 

AMOCs for the inspection requirements of 

this AD only at fastener locations where the 

AMOC provided for installing either 

BACB30NX or BACB30US fasteners.

Issued in Renton, Washington, on January 

21, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–1794 Filed 1–31–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2000–NM–120–AD] 

RIN 2120–AA64

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–120 Series 

Airplanes

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT).

ACTION: Supplemental notice of 

proposed rulemaking; reopening of 

comment period. 

SUMMARY: This document revises an 

earlier proposed airworthiness directive 

(AD), applicable to certain EMBRAER 

Model EMB–120 series airplanes that 

would have required initial and 

repetitive calibration testing of 

potentiometers to detect noisy signals 

and replacement of only those with 

noisy signals. This new action revises 

the proposed AD by reducing the 

compliance time for the repetitive 

calibration testing of the potentiometers 

and adding the requirement for 

reporting results of the calibration tests 

of the potentiometers and the readouts 

of the flight data recorder (FDR) to the 

airplane manufacturer. The actions 

specified by this new proposed AD are 

intended to prevent the potentiometers 

that provide information on the 

positions of the primary flight controls 

to the FDR from transmitting noisy 

signals or becoming improperly 

calibrated, resulting in the transmission 

of incomplete or inaccurate data to the 

FDR. This lack of reliable data could 

hamper discovery of the unsafe 

condition that caused an accident or 

incident and prevent the FAA from 

developing and mandating actions to 

prevent additional accidents or 

incidents caused by that same unsafe 

condition. This action is intended to 

address the identified unsafe condition.

DATES: Comments must be received by 

February 28, 2005.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2000–NM–

120–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9-anmnprmcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2000–NM–120–AD’’ in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER), P.O. Box 343–CEP 12.225, 

Sao Jose dos Campos–SP, Brazil. This 

information may be examined at the 

Federal Aviation Administration (FAA), 

Transport Airplane Directorate, Rules 

Docket, 1601 Lind Avenue, SW., 

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, 1601 

Lind Avenue, S.W., Renton, 

Washington, 98055–4056; telephone 

(425) 227–1175; fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested persons are invited to 

participate in the making of the 

proposed rule by submitting such 

written data, views, or arguments, as 

they may desire. Communications shall 

identify the Rules Docket number and 

be submitted in triplicate to the address 

specified above. All communications 

received on or before the closing date 

for comments, specified above, will be 

considered before taking action on the 

proposed rule. The proposals contained 

in this action may be changed in light 

of the comments received. 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues. 

• For each issue, state what specific 

change to the proposed AD is being 

requested. 

• Include justification (e.g., reasons or 

data) for each request. 

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report 

summarizing each FAA-public contact 

concerned with the substance of this 

proposal will be filed in the Rules 

Docket. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this action 

must submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket Number 2000–NM–120–AD.’’

The postcard will be date stamped and 

returned to the commenter. 

Availability of NPRMs 

Any person may obtain a copy of this 

NPRM by submitting a request to the 

FAA, Transport Airplane Directorate, 

ANM–114, Attention: Rules Docket No. 

2000–NM–120–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056.

Discussion 

A proposal to amend part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) to add an airworthiness 

directive (AD), applicable to certain 

EMBRAER Model EMB–120 series 

airplanes, was published as a 

supplemental notice of proposed 

rulemaking (NPRM) in the Federal 

Register on March 19, 2003 (68 FR 

13239), hereafter referred to as the ‘‘first 

supplemental NPRM.’’ That 

supplemental NPRM would have 

required initial and repetitive 

calibration testing of the potentiometers 

to detect noisy signals and replacement 

of only those with noisy signals. 

Potentiometers that provide information 

on the positions of the primary flight 

controls to the flight data recorder (FDR) 

transmitting noisy signals or becoming 

improperly calibrated, if not corrected, 

could result in the transmission of 

incomplete or inaccurate data to the 

FDR. This lack of reliable data could 

hamper discovery of the unsafe 

condition that caused an accident or 

incident and prevent the FAA from 

developing and mandating actions to 

prevent additional accidents or 

incidents caused by that same unsafe 

condition.