Federal Register / Vol. 70, No. 185 / Monday, September 26, 2005 / Proposed Rules 56145 

proposed AD to require that all those 

airplanes accomplish all the required 

actions. This requirement would ensure 

that the actions specified in both of the 

Israeli airworthiness directives, and 

required by this proposed AD, are 

accomplished on all affected airplanes. 

This difference has been coordinated 

with the CAAI. 

Operators should note that, although 

the Accomplishment Instructions of the 

referenced service bulletins describe 

procedures for submitting a service 

reply card, this proposed AD would not 

require that action. We do not need this 

information from operators. 

Costs of Compliance 

This proposed AD would affect about 

106 airplanes of U.S. registry. The 

proposed inspection would take about 8 

work hours per airplane, at an average 

labor rate of $65 per work hour. Based 

on these figures, the estimated cost of 

the proposed AD for U.S. operators is 

$55,120, or $520 per airplane. 

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 

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 adding 

the following new airworthiness 

directive (AD): 

Gulfstream Aerospace LP (Formerly Israel 

Aircraft Industries, Ltd.): Docket No. 

FAA–2005–22511; Directorate Identifier 

2005–NM–120–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this AD action by 

October 26, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Gulfstream 

Aerospace LP Model Gulfstream 100 

airplanes; and Model Astra SPX, and 1125 

Westwind Astra airplanes; certificated in any 

category; as identified in Gulfstream Alert 

Service Bulletin 100–32A–275, and 

Gulfstream Service Bulletin 1125–11–181, 

both Revision 1, both dated December 24, 

2003. 

Unsafe Condition 

(d) This AD was prompted by reports of 

failure of the steering brackets of the nose 

wheel steering assembly of the landing gear, 

and in one incident, loss of steering control. 

We are issuing this AD to find and fix 

discrepancies of the nose wheel steering 

assembly which could result in loss of 

steering control and consequent reduced 

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. 

One-Time Inspection/Corrective Action 

(f) Within 50 flight hours or 25 landings 

after the effective date of this AD, whichever 

is first: Perform a one-time non-destructive 

test inspection for discrepancies of the nose 

wheel steering assembly, install a warning 

placard on each nose landing gear door, and 

do any applicable corrective action, by 

accomplishing all the actions specified in the 

Accomplishment Instructions of Gulfstream 

Alert Service Bulletin 100–32A–275, and 

Gulfstream Service Bulletin 1125–11–181, 

both Revision 1, both dated December 24, 

2003. Any applicable corrective action must 

be accomplished before further flight in 

accordance with Alert Service Bulletin 100–

32A–275. Although the service bulletins 

specify to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, International Branch, 

Transport Airplane Directorate, FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

Related Information 

(h) Israeli airworthiness directives 32–03–

10–05 R1, effective February 8, 2004, and 32–

03–12–09, effective February 5, 2004, also 

address the subject of this AD. 

Issued in Renton, Washington, on 

September 16, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19141 Filed 9–23–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22510; Directorate 

Identifier 2004–NM–32–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede two existing airworthiness 

directives (ADs), one AD applicable to 

all Boeing Model 747 airplanes and the 

other AD applicable to certain Boeing 

Model 747 airplanes. The first AD 

currently requires repetitive inspections 

for cracking of the upper skin of the 

56146 Federal Register / Vol. 70, No. 185 / Monday, September 26, 2005 / Proposed Rules 

horizontal stabilizer center section and 

the rear spar upper chord, and repair if 

necessary. The other AD currently 

requires repetitive inspections for 

cracking of the upper skin of the 

outboard and center sections of the 

horizontal stabilizer and the rear spar 

structure, hinge fittings, terminal 

fittings, and splice plates; and repair if 

necessary. This proposed AD would 

add, for certain airplanes, repetitive 

inspections for cracking of the outboard 

and center sections of the horizontal 

stabilizer and repair if necessary. For 

certain other airplanes, this proposed 

AD would add a detailed inspection to 

determine the type of fasteners, related 

investigative actions, and repair if 

necessary. This proposed AD also 

would revise the compliance times for 

certain inspections and add alternate 

inspections for cracking of the upper 

skin of the center section and rear spar 

upper chord. This proposed AD is 

prompted by reports of cracking in the 

outboard and center section of the aft 

upper skin of the horizontal stabilizer, 

the rear spar chord, rear spar web, 

terminal fittings, and splice plates; and 

a report of fractured and cracked steel 

fasteners. We are proposing this AD to 

detect and correct this cracking, which 

could lead to reduced structural 

capability of the outboard and center 

sections of the horizontal stabilizer and 

could result in loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by November 10, 

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. 

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 written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2005–22510; Directorate Identifier 

2004–NM–32–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 may 

review the DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78), or you may 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 March 11, 2002, we issued AD 

2002–06–02, amendment 39–12678 (67 

FR 12464, March 19, 2002), for all 

Boeing Model 747 airplanes. That AD 

requires repetitive inspections for 

cracking of the upper skin of the 

horizontal stabilizer center section and 

the rear spar upper chord, and repair, if 

necessary. That AD was prompted by a 

report of cracking found in the upper 

skin of the horizontal center section on 

a Boeing Model 747SR series airplane. 

We issued that AD to find and fix this 

cracking, which could lead to reduced 

structural capability of the horizontal 

stabilizer center section, and result in 

the loss of control of the airplane. 

On June 18, 2003, we issued AD 

2003–13–09, amendment 39–13209 (68 

FR 38583, June 30, 2003), for certain 

Boeing Model 747 airplanes. That AD 

requires repetitive inspections for 

cracking of the upper skin of the 

outboard and center sections of the 

horizontal stabilizer and the rear spar 

structure, hinge fittings, terminal 

fittings, and splice plates; and repair if 

necessary. That AD was prompted by 

reports of cracking on Model 747 

airplanes in areas not covered by certain 

inspections required by AD 2002–06–

02. We issued AD 2003–13–09 to find 

and fix this cracking, which could lead 

to reduced structural capability of the 

outboard and center sections of the 

horizontal stabilizer, and result in loss 

of control of the airplane. 

Actions Since Existing ADs Were Issued 

The preamble to AD 2003–13–09 

explains that we considered the 

requirements ‘‘interim action’’ and were 

considering further rulemaking action. 

We now have determined that further 

rulemaking is indeed necessary, and 

this proposed AD follows from that 

determination. Further rulemaking 

action would supersede AD 2003–13–09 

to address the procedures for repetitive 

inspections of Zone C to find additional 

cracking, and repair of any cracking 

found, as described in Boeing Alert 

Service Bulletin 747–55A2050, Revision 

1, dated May 1, 2003. That further 

rulemaking action would also mandate 

repetitive inspections of Zone B for 

Groups 4, 5, and 6 airplanes. In addition 

to superseding AD 2003–13–09, that 

rulemaking action would also supersede 

AD 2002–06–02 to mandate long-term 

inspections of all affected zones 

specified in the referenced service 

bulletin for all 747 series airplanes. 

Relevant Service Information 

We have previously reviewed Boeing 

Alert Service Bulletin 747–55A2050, 

dated February 28, 2002. The service 

bulletin is cited as the appropriate 

source of service information for 

accomplishing the requirements of AD 

2002–06–02. 

We have also previously reviewed 

Boeing Alert Service Bulletin 747–

55A2050, Revision 1, dated May 1, 

2003. The service bulletin is cited as the 

appropriate source of service 

information for accomplishing the Zone 

A and Zone B inspections required by 

AD 2003–13–09. The service bulletin 

Federal Register / Vol. 70, No. 185 / Monday, September 26, 2005 / Proposed Rules 56147 

also describes Zone C procedures, 

which this proposed AD would require 

for certain airplanes, as follows: 

• Do a magnetic inspection to 

determine if any fastener common to the 

horizontal stabilizer outboard and 

center section upper chords at the hinge 

fitting halves and the splice plate is a 

Maraging or H–11 steel fastener. 

• Do related investigative actions 

(includes ultrasonic, magnetic particle, 

or fluorescent particle inspections for 

any cracked or fractured Maraging or H–

11 steel fastener common to the 

horizontal stabilizer outboard and 

center section upper chords at the hinge 

fitting halves and the splice plate). If no 

crack or fracture is found on a Maraging 

or H–11 steel fastener, the service 

bulletin specifies repeating the related 

investigative and corrective actions, as 

necessary. 

• Do corrective action, if necessary. 

The corrective action includes 

performing the Part 4 open hole NDT 

inspection and replacing the fastener 

with a new, improved fastener. 

Boeing Alert Service Bulletin 747–

55A2050, Revision 1, dated May 1, 

2003, specifies the following repetitive 

compliance times: 

• Zone B NDT inspection for groups 

1, 2, and 3: Repeat within 2,400 flight 

cycles or 13,000 flight hours, whichever 

comes first. 

• Zone B Open hole NDT inspection 

for groups 1 through 6: Repeat within 

8,000 flight cycles or 44,000 flight 

hours, whichever comes first. 

• Zone C ultrasonic inspection of 

magnetic fasteners for groups 1, 2, and 

3: If no crack or fracture is found, repeat 

within 18 months. 

We have determined that 

accomplishment of the actions specified 

in the service information will 

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. Therefore, we are 

proposing this AD, which would 

supersede AD 2002–06–02 to continue 

to require repetitive inspections for 

cracking of the upper skin of the 

horizontal stabilizer center section and 

the rear spar upper chord, and repair, if 

necessary. This proposed AD would 

also supersede AD 2003–13–09 to 

continue to require repetitive 

inspections for cracking of the upper 

skin of the outboard and center sections 

of the horizontal stabilizer and the rear 

spar structure, hinge fittings, terminal 

fittings, and splice plates; and repair if 

necessary. This proposed AD also 

would, for certain airplanes, add 

repetitive inspections for cracking of the 

horizontal stabilizer center and 

outboard section, and repair if 

necessary. For certain other airplanes, 

this proposed AD would add a detailed 

inspection to determine if fasteners are 

Maraging or H–11 steel fasteners, related 

investigative actions, and corrective 

action if necessary. This proposed AD 

also would revise the compliance times 

for certain inspections and add alternate 

high frequency eddy current (HFEC) 

inspections for cracking of the upper 

skin of the center section and rear spar 

upper chord. This proposed AD would 

require you to use Boeing Alert Service 

Bulletin 747–55A2050, dated February 

28, 2002; and Revision 1, dated May 1, 

2003; to perform these actions except as 

discussed under ‘‘Differences Between 

the Proposed AD and the Service 

Bulletins.’’

Differences Between the Proposed AD 

and the Service Bulletins 

The service bulletins 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 we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

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. 

Revision 1 of the service bulletin 

allows operators to re-install certain H–

11 bolts. However, H–11 bolts are 

subject to stress corrosion cracking. We 

have determined that, because of the 

safety implications and consequences 

associated with stress corrosion 

cracking, this proposed AD would 

require that inconel bolts be installed. 

This difference has been coordinated 

with the manufacturer. 

Differences in Compliance Time/ 

Inspections Between the Proposed AD 

and AD 2002–06–02 

Operators should note that AD 2002–

06–02 requires repetitive detailed and 

HFEC inspections, as applicable, at 

intervals not to exceed 1,000 flight 

cycles. This interval matches the 

interval specified in Boeing Alert 

Service Bulletin 747–55A2050, dated 

February 28, 2002, which was 

referenced as the appropriate source of 

service information for accomplishing 

the requirements of AD 2002–06–02. 

However, for the same detailed 

inspections, this proposed AD would 

require repetitive inspections, specified 

as Zone A inspections, at intervals not 

to exceed 1,000 flight cycles or 5,600 

flight hours, whichever occurs first. The 

interval for Zone A inspections matches 

the interval specified in Revision 1, 

dated May 1, 2003, of the service 

bulletin, which is referenced as the 

appropriate source of service 

information for accomplishing the 

requirements of this proposed AD. We 

have determined this interval to be 

appropriate in consideration of the 

safety implications. 

Operators should also note that while 

AD 2002–06–02 requires doing 

repetitive detailed and HFEC 

inspections, as applicable, this proposed 

AD would require doing repetitive 

detailed inspections, specified as Zone 

A inspections, or as an option, doing 

repetitive HFEC inspections, specified 

as Zone B inspections. We have 

determined the Zone A inspections 

ensure an adequate level of safety for 

the affected fleet. The Zone B 

inspections, if done, have a greater 

repetitive inspection interval. 

Differences in Compliance Time 

Between the Proposed AD and AD 

2003–13–09 

Operators should note that, for 

Groups 1, 2, and 3 airplanes, the 

thresholds specified in AD 2003–13–09 

for the Zone B inspections are at the 

later of the following times: 90 days 

after the effective date of the AD; or 

before the accumulation of 27,000 total 

flight cycles or 117,000 total flight 

hours, whichever occurs later. 

However for the same airplanes, this 

proposed AD adds additional thresholds 

specified in paragraph (i)(2) of the 

proposed AD. The new thresholds 

match the thresholds specified in 

Revision 1, dated May 1, 2003, of the 

service bulletin for airplanes with less 

than 27,000 flight cycles and 117,000 

flight hours. Airplanes which have more 

than 27,000 flight cycles and 117,000 

flight hours should have already done 

the Zone B inspections in accordance 

with AD 2003–13–09. We have 

determined these thresholds to be 

appropriate in consideration of the 

safety implications. 

Change to Existing AD 

This proposed AD would retain 

certain requirements of AD 2002–06–02. 

Since AD 2002–06–02 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: 

56148 Federal Register / Vol. 70, No. 185 / Monday, September 26, 2005 / Proposed Rules 

REVISED PARAGRAPH IDENTIFIERS FOR

AD 2002–06–02 

Requirement in AD 

2002–06–02 

Corresponding 

requirement in this 

proposed AD 

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

This proposed AD also would retain 

certain requirements of AD 2003–13–09. 

The corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS FOR

AD 2003–13–09 

Requirement in AD 

2003–13–09 

Corresponding 

requirement in this 

proposed AD 

Paragraph (a) ............ Paragraph (h) 

Paragraph (b) ............ Paragraph (i). 

Costs of Compliance 

This proposed AD would affect about 

1,087 Model 747 airplanes worldwide 

and would affect about 227 airplanes of 

U.S. registry. The following table 

provides the estimated costs for U.S. 

operators to comply with this proposed 

AD. The costs for the inspections are per 

inspection cycle. 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Cost per 

airplane Fleet cost 

Zone A Detailed Inspection (required by AD 2002–06–02) ............................................ 8 $65 $520 $118,040 

Zone A NDT Inspection, if done ...................................................................................... 10 65 650 ....................

Zone B NDT Inspection (required by AD 2003–13–09 for Groups 1, 2, and 3 airplanes) .......................................................................................................................... 8 65 520 ....................

Zone B Open-hole NDT Inspection (new proposed action for Groups 3, 4, and 5 airplanes; and for Groups 1, 2, and 3 airplanes, if done) ............................................... 30 65 1,950 ....................

Zone C Maraging or H–11 Steel Fastener Inspection (new proposed action for 

Groups 1, 2, and 3 airplanes) ...................................................................................... 8 65 520 ....................

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, 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 

proposed 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 39–12678 (67 FR 

12464, March 19, 2002) and amendment 

39–13209 (68 FR 38583, June 30, 2003), 

and adding the following new 

airworthiness directive (AD): 

Boeing: Docket No. FAA–2005–22510; 

Directorate Identifier 2004–NM–32–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this airworthiness 

directive (AD) action by November 10, 2005. 

Affected ADs 

(b) This AD supersedes AD 2002–06–02, 

amendment 39–12678; and AD 2003–13–09, 

amendment 39–13209. 

Applicability 

(c) 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. 

Unsafe Condition 

(d) This AD was prompted by reports of 

cracking in the outboard and center section 

of the aft upper skin of the horizontal 

stabilizer, the rear spar chord, rear spar web, 

terminal fittings, and splice plates; and a 

report of fractured and cracked steel 

fasteners. We are issuing this AD to detect 

and correct this cracking, which could lead 

to reduced structural capability of the 

outboard and center sections of the 

horizontal stabilizer and could result in loss 

of control 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. 

Certain Requirements of AD 2002–06–02: To 

Be Done in Accordance With New Revision 

of the Service Bulletin 

Repetitive Inspections for Zone A 

(f) Before the accumulation of 24,000 total 

flight cycles, or within 90 days after April 3, 

2002 (the effective date of AD 2002–06–02, 

amendment 39–12678), whichever occurs 

Federal Register / Vol. 70, No. 185 / Monday, September 26, 2005 / Proposed Rules 56149 

later: Except as provided by paragraph (l) of 

this AD, ‘‘Optional High Frequency Eddy 

Current (HFEC) Inspections for Zone A,’’ do 

a detailed inspection for cracking of the 

upper skin of the horizontal stabilizer center 

section and the rear spar upper chord, in 

accordance with the Work Instructions and 

Figure 1 of Boeing Alert Service Bulletin 

747–55A2050, dated February 28, 2002; or in 

accordance with Part 1 of the Work 

Instructions of Boeing Alert Service Bulletin 

747–55A2050, Revision 1, dated May 1, 2003. 

(The inspection procedures include a 

detailed inspection for cracking of the upper 

horizontal skin and of the vertical and 

horizontal flanges of the rear spar upper 

chord.) As of the effective date of this AD, 

do the detailed inspection in accordance 

with Part 1 of the Work Instructions of 

Boeing Alert Service Bulletin 747–55A2050, 

Revision 1, dated May 1, 2003. Repeat the 

detailed inspection thereafter at the times 

specified in paragraphs (f)(1) and (f)(2) of this 

AD, as applicable. 

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 mirrors, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

(1) For airplanes on which the detailed 

inspection required by paragraph (a) of AD 

2002–06–02 has been done before the 

effective date of this AD: Within 1,000 flight 

cycles after the last detailed inspection, do 

the detailed inspection specified in 

paragraph (f) of this AD and repeat the 

detailed inspection specified in paragraph (f) 

of this AD thereafter at intervals not to 

exceed 1,000 flight cycles or 5,600 flight 

hours, whichever comes first. 

(2) For airplanes on which the detailed 

inspection required by paragraph (a) of AD 

2002–06–02 has not been done before the 

effective date of this AD: After accomplishing 

the initial inspection, repeat the detailed 

inspection specified in paragraph (f) of this 

AD thereafter at intervals not to exceed 1,000 

flight cycles or 5,600 flight hours, whichever 

comes first. 

Requirements of AD 2003–13–09 With New 

Compliance Times Required by This AD 

Repetitive Inspections for Zone B: Groups 1 

Through 3 

(g) For Groups 1, 2, and 3 airplanes 

identified in paragraph 1.A. Effectivity of 

Boeing Alert Service Bulletin 747–55A2050, 

Revision 1, dated May 1, 2003: At the time 

specified in paragraph (h) of this AD, do the 

Zone B inspections, as required by either 

paragraph (g)(1) or (g)(2) of this AD, in 

accordance with the Work Instructions of 

Boeing Alert Service Bulletin 747–55A2050, 

Revision 1, dated May 1, 2003, except as 

provided by paragraph (n) of this AD. Repeat 

the applicable inspection at the applicable 

time specified in Sheet 2 of Figure 1 of the 

service bulletin. 

(1) Do nondestructive test (NDT) 

inspections for cracking of the upper skin of 

the outboard and center sections of the 

horizontal stabilizer and the rear spar 

structure, hinge fittings, terminal fittings, and 

splice plates, in accordance with Part 3 of the 

service bulletin. The inspections include an 

ultrasonic inspection of the outboard and 

center sections, rear spar upper chords under 

the hinge fitting halves, upper skins under 

the splice plates, and the rear spar webs 

behind the terminal fittings; a HFEC 

inspection of the terminal fitting around the 

fasteners; a low frequency eddy current 

inspection of the splice plates around the 

fasteners; a surface HFEC inspection of the 

rear spar upper chords in the radius area 

above the terminal fitting and the lower 

surface of the horizontal flange; and an HFEC 

inspection of the rear spar webs in the 

exposed area above the terminal fitting. 

(2) In lieu of the inspections specified in 

paragraph (g)(1) of this AD: Do an alternate 

open hole HFEC inspection for cracking of 

the splice plates, terminal fittings, hinge 

fitting halves, rear spar upper chords, rear 

spar webs, and upper skins; and replace H–

11 bolts with inconel bolts; in accordance 

with Part 4 of the service bulletin, except as 

provided by paragraph (n) of this AD. 

(h) For Groups 1, 2, and 3 airplanes 

identified in paragraph 1.A. Effectivity of 

Boeing Alert Service Bulletin 747–55A2050, 

Revision 1, dated May 1, 2003: Do the 

inspections required by paragraph (g) of this 

AD at the earlier of the times specified in 

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

(1) At the later of the times specified in 

paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. 

(i) Before the accumulation of 27,000 total 

flight cycles or 117,000 total flight hours, 

whichever is first. 

(ii) Within 90 days after July 15, 2003 (the 

effective date of AD 2003–13–09, amendment 

39–13209). 

(2) At the applicable times specified in 

paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. 

(i) For Groups 1 and 3 airplanes identified 

in paragraph 1.A. Effectivity of Boeing Alert 

Service Bulletin 747–55A2050, Revision 1, 

dated May 1, 2003: At the latest of the times 

specified in paragraphs (h)(2)(i)(A) and 

(h)(2)(i)(B) of this AD. 

(A) Before the accumulation of 20,000 total 

flight cycles or 85,000 total flight hours, 

whichever is first. 

(B) Within 12 months after the effective 

date of this AD. 

(ii) For Group 2 airplanes identified in 

paragraph 1.A. Effectivity of Boeing Alert 

Service Bulletin 747–55A2050, Revision 1, 

dated May 1, 2003: At the latest of the times 

specified in paragraphs (h)(2)(ii)(A) and 

(h)(2)(ii)(B) of this AD. 

(A) Before the accumulation of 22,000 total 

flight cycles or 95,000 total flight hours, 

whichever is first. 

(B) Within 12 months after the effective 

date of this AD. 

Additional Requirements of This AD 

Repetitive Inspections for Zone B: Groups 4 

Through 6 

(i) For Groups 4, 5, and 6 airplanes 

identified in paragraph 1.A. Effectivity of 

Boeing Alert Service Bulletin 747–55A2050, 

Revision 1, dated May 1, 2003: At the later 

of the times specified in paragraphs (i)(1) and 

(i)(2) of this AD, do the Zone B inspections 

as specified in paragraph (g)(2) of this AD. 

Repeat the applicable inspection at the 

applicable time specified in Sheet 3 of Figure 

1 of the service bulletin. 

(1) Before the accumulation of 20,000 total 

flight cycles or 85,000 total flight hours, 

whichever is first. 

(2) Within 12 months after the effective 

date of this AD. 

Repetitive Inspections for Zone C: Groups 1 

Through 3 

(j) For Groups 1, 2, and 3 airplanes 

identified in paragraph 1.A. Effectivity of 

Boeing Alert Service Bulletin 747–55A2050, 

Revision 1, dated May 1, 2003: Within 18 

months after the effective date of this AD, do 

a detailed inspection to determine if fasteners 

common to the horizontal stabilizer outboard 

and center section upper chords at the hinge 

fitting halves and the splice plates are 

magnetic, related investigative actions 

(includes ultrasonic, magnetic particle, or 

fluorescent particle inspections for any 

cracked or fractured Maraging or H–11 steel 

fastener), and corrective actions by 

accomplishing all the actions specified in 

Part 5 of the Work Instructions of the service 

bulletin, except as provided by paragraph (n) 

of this AD. 

(k) If, during the actions required by 

paragraph (j) of this AD, any fastener is found 

to be magnetic and is not cracked or 

fractured, repeat the related investigative 

actions and corrective actions specified in 

paragraph (j) of this AD at the time specified 

in Sheet 4 of Figure 1 of Boeing Alert Service 

Bulletin 747–55A2050, Revision 1, dated 

May 1, 2003. 

Optional High Frequency Eddy Current 

(HFEC) Inspections for Zone A 

(l) In lieu of the detailed inspection 

specified in paragraph (f) of this AD: Do an 

HFEC inspection for cracking of the upper 

skin of the horizontal stabilizer center section 

and the rear spar upper chord, in accordance 

with Part 2 of the Work Instructions of 

Boeing Alert Service Bulletin 747–55A2050, 

Revision 1, dated May 1, 2003. Repeat the 

HFEC inspection thereafter at intervals not to 

exceed 2,700 flight cycles or 15,000 flight 

hours, whichever comes first. 

Repair 

(m) If any discrepancy (cracking or 

damage) is found during any inspection or 

related investigative action required by 

paragraphs (f), (g), (i), or (l) of this AD: Before 

further flight, repair in accordance with the 

Work Instructions of Boeing Alert Service 

Bulletin 747–55A2050, Revision 1, dated 

May 1, 2003, except as provided by 

paragraph (n) of this AD. Where the service 

bulletin specifies to contact the manufacturer 

for appropriate action: Before further flight, 

repair according to a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA; or according to data meeting the 

certification basis of the airplane 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 

56150 Federal Register / Vol. 70, No. 185 / Monday, September 26, 2005 / Proposed Rules 

the airplane, and the approval must 

specifically refer to this AD. 

Parts Installation 

(n) As of the effective date of this AD, no 

person may install any Maraging or H–11 

steel fasteners in the locations specified in 

this AD. Where Boeing Alert Service Bulletin 

747–55A2050, Revision 1, dated May 1, 2003, 

specifies to install H–11 bolts (kept 

fasteners), this AD requires installation of 

inconel bolts. 

Alternative Methods of Compliance (AMOCs) 

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

the authority to approve AMOCs for this AD, 

if requested using 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) AMOCs, approved previously per AD 

2002–06–02, amendment 39–12678; or AD 

2003–13–09, amendment 39–13209; are 

approved as AMOCs for the corresponding 

provisions of this AD, for the repaired area 

only. 

Issued in Renton, Washington, on 

September 16, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19142 Filed 9–23–05; 8:45 am] 

BILLING CODE 4910–13–P 

ENVIRONMENTAL PROTECTION 

AGENCY 

40 CFR Part 271 

[FRL–7974–2] 

North Dakota: Final Authorization of 

State Hazardous Waste Management 

Program Revision 

AGENCY: Environmental Protection 

Agency (EPA). 

ACTION: Proposed rule. 

SUMMARY: The EPA proposes to grant 

Final authorization to the hazardous 

waste program changes submitted by 

North Dakota. In the ‘‘Rules’’ section of 

this Federal Register, we are 

authorizing the State’s program changes 

as an immediate final rule without a 

prior proposed rule because we believe 

this action as not controversial. Unless 

we get written comments opposing this 

authorization during the comment 

period, the immediate final rule will 

become effective and the Agency will 

not take further action on this proposal. 

If we receive comments that oppose this 

action, we will publish a document in 

the Federal Register withdrawing this 

rule before it takes effect. EPA will 

address public comments in a later final 

rule based on this proposal. EPA may 

not provide further opportunity for 

comment. Any parties interested in 

commenting on this action must do so 

at this time. 

DATES: We must receive your comments 

by October 26, 2005. 

ADDRESSES: Submit your comments by 

one of the following methods: 1. Federal 

eRulemaking Portal: http:// 

www.regulations.gov. Follow the on-line 

instructions for submitting comments. 2. 

E-mail: shurr.kris@epa.gov. 3. Mail: Kris 

Shurr, 8P–HW, U.S. EPA, Region 8, 999 

18th St, Ste 300, Denver, Colorado 

80202–2466, phone number: (303) 312–

6139. 4. Hand Delivery or Courier: to 

Kris Shurr, 8P–HW, U.S. EPA, Region 8, 

999 18th St, Ste 300, Denver, Colorado 

80202–2466, phone number: (303) 312–

6139. 

Instructions: Do not submit 

information that you consider to be CBI 

or otherwise protected through 

regulations.gov, or e-mail. The Federal 

regulations.gov Web site is an 

‘‘anonymous access’’ system which 

means EPA will not know your identity 

or contact information unless you 

provide it in the body of your comment. 

If you send an e-mail comment directly 

to EPA without going through 

regulations.gov, your e-mail address 

will be automatically captured and 

included as part of the comment that is 

placed in the public docket and made 

available on the Internet. If you submit 

an electronic comment, EPA 

recommends that you include your 

name and other contact information in 

the body of your comment and with any 

disk or CD–ROM you submit. If EPA 

cannot read your comment due to 

technical difficulties and cannot contact 

you for clarification, EPA may not be 

able to consider your comment. 

Electronic files should avoid the use of 

special characters, any form of 

encryption, and be free of any defects or 

viruses. 

You can view and copy North 

Dakota’s application at the following 

addresses: NDDH from 9 a.m. to 4 p.m., 

1200 Missouri Ave, Bismarck, ND 

58504–5264, contact: Curt Erickson, 

phone number (701) 328–5166 and EPA 

Region 8, from 8 a.m. to 3 p.m., 999 18th 

Street, Suite 300, Denver, CO 80202–

2466, contact: Kris Shurr, phone 

number: (303) 312–6139, e-mail: 

shurr.kris@epa.gov. 

FOR FURTHER INFORMATION CONTACT: Kris 

Shurr, EPA Region 8, 999 18th Street, 

Suite 300, Denver, Colorado 80202–

2466, phone number: (303) 312–6139, email: shurr.kris@epa.gov. 

SUPPLEMENTARY INFORMATION: For 

additional information, please see the 

immediate final rule published in the 

‘‘Rules’’ section of this Federal Register. 

Dated: September 19, 2005. 

Robert E. Roberts, 

Regional Administrator, Region 8. 

[FR Doc. 05–19137 Filed 9–23–05; 8:45 am] 

BILLING CODE 6560–50–P 

FEDERAL COMMUNICATIONS 

COMMISSION 

47 CFR Part 79 

[CG Docket No. 05–231; FCC 05–142] 

Closed Captioning of Video 

Programming; Telecommunications for 

the Deaf, Inc. Petition for Rulemaking 

AGENCY: Federal Communications 

Commission. 

ACTION: Proposed rule. 

SUMMARY: In this document, the 

Commission grants a petition for 

rulemaking and initiates a proceeding to 

examine the Commission’s closed 

captioning rules. Specifically, the 

Commission seeks comment on the 

current status of the Commission’s 

closed captioning rules in ensuring that 

video programming is accessible to deaf 

and hard of hearing Americans and 

whether any revisions should be made 

to enhance the effectiveness of those 

rules; and several compliance and 

quality issues relating to closed 

captioning that were raised in a Petition 

for Rulemaking filed by 

Telecommunications for the Deaf, Inc., 

(TDI), the National Association of the 

Deaf, Self Help for Hard of Hearing 

People, Inc., the Association for Late 

Deafened Adults, and the Deaf and Hard 

of Hearing Consumer Advocacy 

Network. 

DATES: Comments are due on or before 

November 10, 2005. Reply comments 

are due on or before November 25, 2005. 

Written comments on the Paperwork 

Reduction Act (PRA) proposed 

information collection requirements 

must be submitted by the general 

public, Office of Management and 

Budget (OMB), and other interested 

parties on or before November 25, 2005. 

ADDRESSES: You may submit comments, 

identified by [docket number and/or 

rulemaking number], by any of the 

following methods: 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

• Federal Communications 

Commission’s Web Site: http:// 

www.fcc.gov/cgb/ecfs/. Follow the 

instructions for submitting comments.