12136 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27525; Directorate 

Identifier 2006–NM–159–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–300, 

747–400, 747–400D, 747SR, and 747SP 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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 airplanes. The 

existing AD currently requires repetitive 

inspections to detect cracks and/or 

corrosion of the girt bar support fitting 

at certain main entry doors (MED), and 

repair or replacement of the support 

fitting. The existing AD also provides 

for various terminating actions for the 

repetitive inspections. This proposed 

AD would require the following 

additional actions: An inspection, for 

certain airplanes, for correct installation 

of square and conical washers in the girt 

bar support fitting; an inspection, for 

certain other airplanes, to determine if 

the washers are installed; and related 

investigative and corrective action if 

necessary. This proposed AD results 

from a report that the square and conical 

washers may be installed incorrectly in 

the girt bar support fitting on airplanes 

on which the support fitting was 

repaired or replaced in accordance with 

the requirements of the existing AD. We 

are proposing this AD to detect and 

correct corrosion of the girt bar support 

fitting, which could result in separation 

of the escape slide from the lower door 

sill during deployment, and 

subsequently prevent proper operation 

of the escape slides at the main entry 

doors during an emergency. We are also 

proposing this AD to detect and correct 

incorrect installation of the square and 

conical washers in the girt bar support 

fitting, which could result in failure of 

the escape slide when deployed. 

DATES: We must receive comments on 

this proposed AD by April 30, 2007. 

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. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Patrick Gillespie, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6429; 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 in the 

ADDRESSES section. Include the docket 

number ‘‘Docket No. FAA–2007–27525; 

Directorate Identifier 2006–NM–159–

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 that 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 may 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 Docket 

Management System receives them. 

Discussion 

On October 31, 1996, we issued AD 

96–23–05, amendment 39–9810 (61 FR 

58318, November 14, 1996), for certain 

Boeing Model 747 series airplanes. That 

AD requires repetitive inspections to 

detect cracks and/or corrosion of the girt 

bar support fitting at certain main entry 

doors (MED); and repair or replacement 

of the support fitting. That AD also 

provides for various terminating actions 

for the repetitive inspections. That AD 

resulted from reports that, during 

scheduled deployment tests of main 

entry door slides, corrosion was found 

on the floor structure supports for the 

escape slides of the main deck entry 

doors on these airplanes. We issued that 

AD to prevent such corrosion, which 

could result in separation of the escape 

slide from the lower door sill during 

deployment, and subsequently prevent 

proper operation of the escape slides at 

the main entry doors during an 

emergency. 

Actions Since Existing AD Was Issued 

Since we issued AD 96–23–05, Boeing 

has determined that the square and 

conical washers may be installed 

incorrectly in the girt bar support fitting 

on airplanes on which the support 

fitting was repaired or replaced in 

accordance with Boeing Service Bulletin 

747–53A2378, dated June 24, 1993; 

Revision 1, dated March 10, 1994; or 

Revision 2, dated July 24, 2003 

(Revision 1 of the service bulletin was 

referenced as the appropriate source of 

service information for doing the actions 

specified in AD 96–23–05). 

Relevant Service Information 

We have reviewed Boeing Service 

Bulletin 747–53A2378, Revision 3, 

dated August 11, 2005. The service 

bulletin contains essentially the same 

procedures for the actions described in 

the earlier revisions of the service 

bulletin, but Revision 3 revises the 

procedures for the installation of the 

square and conical washers on the girt 

bar support fitting. 


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Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules 12137 

Revision 3 also adds actions for 

airplanes on which the support fitting 

was replaced or repaired in accordance 

with any earlier revision of the service 

bulletin: 

• For Groups 7, 8, and 9 airplanes 

identified in the service bulletin: Do an 

inspection for correct installation of 

square and conical washers in the girt 

bar floor fitting, related investigative 

action, and corrective actions. The 

related investigative action is an 

inspection of the bolts and washers for 

damage. The corrective actions include 

installing the square and conical 

washers correctly and contacting the 

manufacturer if damage is found. 

• For Groups 1 through 6 airplanes 

identified in the service bulletin: Do an 

inspection to check if square and 

conical washers are installed in the girt 

bar floor fitting, related investigative 

actions, and corrective actions. The 

related investigative actions include 

doing an inspection for correct 

installation of square and conical 

washers in the girt bar floor fitting and 

an inspection of the bolts and washers 

for damage. The corrective actions 

include installing the square and 

conical washers correctly and 

contacting the manufacturer if damage 

is found. 

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 develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 96–23–

05 and would retain the requirements of 

the existing AD. This proposed AD 

would also require the following actions 

for airplanes on which the support 

fitting was repaired or replaced in 

accordance with Boeing Service Bulletin 

747–53A2378, dated June 24, 1993; 

Revision 1, dated March 10, 1994; or 

Revision 2, dated July 24, 2003: An 

inspection, for certain airplanes, for 

correct installation of square and 

conical washers in the girt bar support 

fitting; an inspection, for certain other 

airplanes, to determine if the washers 

are installed; and related investigative 

and corrective action if necessary. 

Differences Between the Proposed AD 

and the Service Bulletin 

Although Boeing Service Bulletin 

747–53A2378 specifies that operators 

may contact the manufacturer if certain 

damage is found, this proposed AD 

would require operators to repair those 

conditions using a method approved by 

the FAA. 

Although Boeing Service Bulletin 

747–53A2378, Revision 3, specifies 

doing certain actions if Boeing Service 

Bulletin 747–53A2378, dated June 24, 

1993; Revision 1, dated March 10, 1994; 

or Revision 2, dated July 24, 2003; was 

accomplished, this proposed AD would 

require those actions to also be done if 

Boeing Service Bulletin 747–25A2831, 

dated August 29, 1991, was 

accomplished. Paragraph (m) of AD 96–

23–05 allows installation of the girt bar 

fitting in accordance with Boeing 

Service Bulletin 747–25A2831 as an 

acceptable method of compliance. 

Therefore, installations done in 

accordance with Boeing Service Bulletin 

747–25A2831 should also be inspected 

for incorrect installation of the square 

and conical washers in the girt bar 

support fitting. 

Change to Existing AD 

This proposed AD would retain all 

requirements of AD 96–23–05. Since AD 

96–23–05 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 

96–23–05 

Corresponding 

requirement in this 

proposed AD 

Note 1 ....................... paragraph (f). 

paragraph (a) ............ paragraph (g). 

paragraph (b) ............ paragraph (h). 

paragraph (c) ............ paragraph (i). 

paragraph (d) ............ paragraph (j). 

paragraph (e) ............ paragraph (k). 

paragraph (f) ............. paragraph (l). 

paragraph (g) ............ paragraph (m). 

paragraph (h) ............ paragraph (n). 

paragraph (i) ............. paragraph (o). 

paragraph (j) ............. paragraph (p). 

paragraph (k) ............ paragraph (q). 

paragraph (l) ............. paragraph (r). 

paragraph (m) ........... paragraph (s). 

Note 2 and paragraph (o) of AD 96–

23–05 have been removed from this 

proposed AD. On July 10, 2002, the 

FAA issued a new version of 14 CFR 

part 39 (67 FR 47997, July 22, 2002), 

which governs the FAA’s airworthiness 

directives system. The regulation now 

includes material that relates to altered 

products and alternative methods of 

compliance (AMOCs), as well as special 

flight permits (e.g., ferry flights). 

Clarification of Doors Affected by the 

Proposed AD 

We have also revised Note 1 of AD 

96–23–05, which has the corresponding 

requirement in paragraph (f) of this 

proposed AD. We have added the 

statement ‘‘the requirements of this AD 

are also not applicable to doors on 

airplanes converted to an all-cargo 

configuration.’’

Explanation of Change to Applicability 

We have revised the applicability of 

the existing AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. Special freighters are 

not identified in the type certificate data 

sheet so the phrase ‘‘special freighters’’

has been removed from the 

applicability. However, as stated 

previously, we have added a statement 

to exempt doors on airplanes converted 

to an all-cargo configuration. 

Explanation of Change Made to Existing 

Requirements 

We have changed all references to a 

‘‘detailed visual inspection’’ in the 

existing AD to ‘‘detailed inspection’’ in 

this proposed AD. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Costs of Compliance 

There are about 1,012 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. The 

average labor rate per hour is $80. The 

cost varies depending on the 

configuration of the airplane. 


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12138 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules 

ESTIMATED COSTS

Action Work hours Cost per airplane Number of U.S.-registered 

airplanes Fleet cost 

Inspection of MEDs (required by AD 96–23–05).Between 88 and 102 ......... Between $7,040 and 

$8,160, per inspection 

cycle.

169 .................................... Between $1,189,760 and 

$1,379,040, per inspection cycle. 

Inspection for correct installation (new proposed 

action).

6 ........................................ $480 .................................. Up to 169 .......................... Up to $81,120. 

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 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, 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–9810 (61 

FR 58318, November 14, 1996) and 

adding the following new airworthiness 

directive (AD): 

Boeing: Docket No. FAA–2007–27525; 

Directorate Identifier 2006–NM–159–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by April 30, 2007. 

Affected ADs 

(b) This AD supersedes AD 96–23–05. 

Applicability 

(c) This AD applies to Boeing Model 747–

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

747–200C, 747–300, 747–400, 747–400D, 

747SR, and 747SP series airplanes, 

certificated in any category, line numbers 1 

through 868 inclusive. 

Unsafe Condition 

(d) This AD results from reports that, 

during scheduled deployment tests of main 

entry door slides, corrosion was found on the 

floor structure supports for the escape slides 

of the main deck entry doors on these 

airplanes. This AD also results from a report 

that the square and conical washers may be 

installed incorrectly in the girt bar support 

fitting on airplanes on which the support 

fitting was repaired or replaced in 

accordance with the requirements of AD 96–

23–05. We are issuing this AD to detect and 

correct corrosion of the girt bar support 

fitting, which could result in separation of 

the escape slide from the lower door sill 

during deployment, and subsequently 

prevent proper operation of the escape slides 

at the main entry doors during an emergency. 

We are also issuing this AD to detect and 

correct incorrect installation of the square 

and conical washers in the girt bar support 

fitting, which could result in failure of the 

escape slide when deployed. 

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. 

Restatement of Requirements of AD 96–23–

05 With New Service Information 

Doors Exempt From/Affected by This AD 

(f) The requirements of this AD are not 

applicable to doors where an escape slide or 

slide/raft is not installed or is not used for 

passenger egress (such as a deactivated door 

3, at doors 4 and/or 5 of an airplane being 

operated in the ‘‘combi’’ configuration, or 

any door not used for passenger egress in a 

‘‘convertible’’ (an airplane configured for 

quick change from passenger to cargo)). The 

requirements of this AD are also not 

applicable to doors on airplanes converted to 

an all-cargo configuration. The requirements 

of this AD become applicable at the time 

when an escape slide or slide/raft is installed 

on such doors, or when such doors are 

activated and/or converted for passenger use. 

The requirements also become applicable at 

the time an airplane operating in an all-cargo 

configuration is converted to a passenger or 

passenger/cargo configuration. 

Inspections and Corrective Actions for 

Airplanes Equipped With Main Entry Door 

(MED) 1 

(g) For airplanes equipped with MED 1: 

Prior to the accumulation of 16 years of 

service since date of manufacture of the 

airplane, or within 18 months after December 

16, 1996 (the effective date of AD 96–23–05), 

whichever occurs later, perform a detailed 

inspection to detect cracking and/or 

corrosion of the girt bar support fitting at the 

left and right MED 1, in accordance with 

Boeing Service Bulletin 747–53A2378, 

Revision 1, dated March 10, 1994; or Boeing 

Service Bulletin 747–53A2378, Revision 3, 

dated August 11, 2005. After the effective 

date of this AD, only Revision 3 may be used. 

(h) If no cracking or corrosion is found 

during the inspection required by paragraph 

(g) of this AD, prior to further flight, 

accomplish either paragraph (h)(1) or (h)(2) 

of this AD, in accordance with the applicable 

instructions specified in Boeing Service 

Bulletin 747–53A2378, Revision 1, dated 

March 10, 1994; or Boeing Service Bulletin 


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Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules 12139 

747–53A2378, Revision 3, dated August 11, 

2005. After the effective date of this AD, only 

Revision 3 may be used. 

(1) Install a new fitting with new fasteners, 

and reinstall the threshold assembly with 

new corrosion-resistant fasteners, in 

accordance with the service bulletin. After 

these actions are accomplished, no further 

action is required by paragraph (h) of this 

AD; or 

(2) Reinstall the threshold assembly with 

corrosion-resistant fasteners, in accordance 

with the service bulletin. Thereafter, repeat 

the inspection required by paragraph (g) of 

this AD at intervals not to exceed 6 years. 

(i) If any cracking is found during the 

inspection required by paragraph (g) or (h)(2) 

of this AD, prior to further flight, install a 

new fitting with new fasteners, and reinstall 

the threshold assembly with new corrosionresistant fasteners, in accordance with Boeing 

Service Bulletin 747–53A2378, Revision 1, 

dated March 10, 1994; or Boeing Service 

Bulletin 747–53A2378, Revision 3, dated 

August 11, 2005. After the effective date of 

this AD, only Revision 3 may be used. After 

these actions are accomplished, no further 

action is required by this paragraph. 

(j) If any corrosion is found during the 

inspection required by paragraph (g) or (h)(2) 

of this AD, prior to further flight, accomplish 

either paragraph (j)(1) or (j)(2) of this AD, in 

accordance with Boeing Service Bulletin 

747–53A2378, Revision 1, dated March 10, 

1994; or Boeing Service Bulletin 747–

53A2378, Revision 3, dated August 11, 2005. 

After the effective date of this AD, only 

Revision 3 may be used. 

(1) Install a new fitting with new fasteners, 

and reinstall the threshold assembly with 

new corrosion-resistant fasteners in 

accordance with the service bulletin. After 

these actions are accomplished, no further 

action is required by this paragraph; or 

(2) Blend out corrosion in accordance with 

the service bulletin. 

(i) If blend out of corrosion is beyond 10 

percent of original thickness or any crack is 

found during accomplishment of the blend 

out procedures, install a new fitting with new 

fasteners, and reinstall the threshold 

assembly with new corrosion-resistant 

fasteners, in accordance with the service 

bulletin. After these actions are 

accomplished, no further action is required 

by this paragraph. 

(ii) If blend out of corrosion does not 

exceed 10 percent of original material 

thickness, accomplish either paragraph 

(j)(2)(ii)(A) or (j)(2)(ii)(B) of this AD: 

(A) Install a new fitting with new fasteners, 

and reinstall threshold assembly with new 

corrosion-resistant fasteners, in accordance 

with the service bulletin. After these actions 

are accomplished, no further action is 

required by this paragraph; or 

(B) Install the repaired fitting with new 

fasteners and reinstall the threshold assembly 

with corrosion-resistant fasteners, in 

accordance with the service bulletin. 

Thereafter, repeat the inspection and 

applicable corrective actions required by 

paragraph (g) of this AD at intervals not to 

exceed 6 years. 

Inspections and Corrective Actions for 

Airplanes Equipped With MED 2, 4, and/or 

5 (MED 2, 3, and/or 4 on Model 747SP Series 

Airplanes) 

(k) For airplanes equipped with MED 2, 4, 

and/or 5 (MED 2, 3, and/or 4 on Model 747SP 

series airplanes): Prior to the accumulation of 

10 years of service since date of manufacture 

of the airplane, or within 18 months after 

December 16, 1996, whichever occurs later, 

perform a detailed inspection to detect 

cracking and/or corrosion of the girt bar 

support fitting at the left and right MED 2, 

4, and 5 (MED 2, 3, and 4 on Model 747SP 

series airplanes), in accordance with Boeing 

Service Bulletin 747–53A2378, Revision 1, 

dated March 10, 1994; or Boeing Service 

Bulletin 747–53A2378, Revision 3, dated 

August 11, 2005. After the effective date of 

this AD, only Revision 3 may be used. 

(l) If no cracking or corrosion is found 

during the inspection required by paragraph 

(k) of this AD, prior to further flight, 

accomplish either paragraph (l)(1) or (l)(2) of 

this AD, in accordance with the applicable 

instructions in Boeing Service Bulletin 747–

53A2378, Revision 1, dated March 10, 1994; 

or Boeing Service Bulletin 747–53A2378, 

Revision 3, dated August 11, 2005. After the 

effective date of this AD, only Revision 3 may 

be used. 

(1) Remove the inspected fitting and 

reinstall it with a new coat of primer and 

new fasteners; and reinstall the threshold 

assembly with new corrosion-resistant 

fasteners; in accordance with the service 

bulletin. After these actions are 

accomplished, no further action is required 

by this paragraph; or 

(2) Reinstall the serrated plate assembly 

and the girt bar floor fitting with corrosionresistant fasteners, in accordance with the 

service bulletin. Thereafter, repeat the 

inspection required by paragraph (k) of this 

AD at intervals not to exceed 6 years. 

(m) If any cracking is found during the 

inspection required by paragraph (k) or (l)(2) 

of this AD, prior to further flight, install a 

new fitting with new fasteners, and reinstall 

the threshold assembly with new corrosionresistant fasteners, in accordance with Boeing 

Service Bulletin 747–53A2378, Revision 1, 

dated March 10, 1994; or Boeing Service 

Bulletin 747–53A2378, Revision 3, dated 

August 11, 2005. After the effective date of 

this AD, only Revision 3 may be used. After 

these actions are accomplished, no further 

action is required by this paragraph. 

(n) If any corrosion is found during the 

inspection required by paragraph (k) or (l)(2) 

of this AD, prior to further flight, accomplish 

either paragraph (n)(1) or (n)(2) of this AD, 

in accordance with Boeing Service Bulletin 

747–53A2378, Revision 1, dated March 10, 

1994; or Boeing Service Bulletin 747–

53A2378, Revision 3, dated August 11, 2005. 

After the effective date of this AD, only 

Revision 3 may be used. 

(1) Install a new fitting with new fasteners, 

and reinstall the threshold assembly with 

new corrosion-resistant fasteners, in 

accordance with the service bulletin. After 

these actions are accomplished, no further 

action is required by this paragraph; or 

(2) Blend out corrosion in accordance with 

the service bulletin. 

(i) If blend out of corrosion is beyond 10 

percent of original thickness or any crack is 

found during accomplishment of the blend 

out procedures, install a new fitting with new 

fasteners, and reinstall the threshold 

assembly with new corrosion-resistant 

fasteners, in accordance with the service 

bulletin. After these actions are 

accomplished, no further action is required 

by this paragraph. 

(ii) If blend out of corrosion does not 

exceed 10 percent of original material 

thickness, install the repaired fitting with 

new fasteners, and reinstall the threshold 

assembly with new corrosion-resistant 

fasteners, in accordance with the service 

bulletin. After these actions are 

accomplished, no further action is required 

by this paragraph. 

(o) For airplanes equipped with main entry 

door (MED) 3 (this paragraph does not apply 

to Model 747SP series airplanes): Prior to the 

accumulation of 16 years of service since 

date of manufacture of the airplane, or within 

18 months after December 16, 1996, 

whichever occurs later, perform a detailed 

inspection to detect cracking and/or 

corrosion of the girt bar support angles at the 

left and right MED 3, in accordance with 

Boeing Service Bulletin 747–53A2378, 

Revision 1, dated March 10, 1994; or Boeing 

Service Bulletin 747–53A2378, Revision 3, 

dated August 11, 2005. After the effective 

date of this AD, only Revision 3 may be used. 

(p) If no cracking or corrosion is found 

during the inspection required by paragraph 

(o) of this AD, prior to further flight, 

accomplish either paragraph (p)(1) or (p)(2) 

of this AD in accordance with the applicable 

instructions in Boeing Service Bulletin 747–

53A2378, Revision 1, dated March 10, 1994; 

or Boeing Service Bulletin 747–53A2378, 

Revision 3, dated August 11, 2005. After the 

effective date of this AD, only Revision 3 may 

be used. 

(1) Remove the inspected angle and 

reinstall it with a new coat of primer and 

new fasteners; and reinstall the threshold 

assembly with new corrosion-resistant 

fasteners; in accordance with the service 

bulletin. After these actions are 

accomplished, no further action is required 

by this paragraph; or 

(2) Reinstall the corner scuff plate and the 

threshold apron with corrosion-resistant 

fasteners, in accordance with the service 

bulletin. Thereafter, repeat the inspection 

required by paragraph (o) of this AD at 

intervals not to exceed 6 years. 

(q) If any crack common to the support 

angles is found during the inspection 

required by paragraph (o) or (p)(2) of this AD, 

prior to further flight, accomplish the actions 

specified in paragraph (q)(1) or (q)(2), as 

applicable, in accordance with Boeing 

Service Bulletin 747–53A2378, Revision 1, 

dated March 10, 1994; or Boeing Service 

Bulletin 747–53A2378, Revision 3, dated 

August 11, 2005. After the effective date of 

this AD, only Revision 3 may be used: 

(1) Install the new angles with new 

fasteners, and reinstall the threshold 

assembly with new corrosion-resistant 

fasteners. After these actions are 

accomplished, no further action is required 

by this paragraph of this AD; or 


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12140 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Proposed Rules 

(2) For any cracking found only in the 

corner casting as specified in the service 

bulletin, accomplish either paragraph (q)(2)(i) 

or (q)(2)(ii) prior to further flight: 

(i) Replace the corner casting in accordance 

with the service bulletin; or 

(ii) Repair the cracked part in accordance 

with a method approved by the Manager, 

Seattle Aircraft Certification Office (ACO), 

FAA, Transport Airplane Directorate. Refer to 

paragraph (w) of this AD for the appropriate 

procedure for seeking such an approval. 

(This option is provided in order to give 

operators time to obtain a replacement corner 

casing without grounding an airplane.) This 

repair is considered temporary action only; 

replacement of the corner casting eventually 

must be accomplished in accordance with a 

schedule prescribed by the Manager, Seattle 

ACO. 

(r) If any corrosion is found during the 

inspection required by paragraph (o) of this 

AD, prior to further flight, accomplish either 

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

accordance with Boeing Service Bulletin 

747–53A2378, Revision 1, dated March 10, 

1994; or Boeing Service Bulletin 747–

53A2378, Revision 3, dated August 11, 2005. 

After the effective date of this AD, only 

Revision 3 may be used. 

(1) Install the new angles with new 

fasteners, and reinstall the threshold 

assembly with new corrosion-resistant 

fasteners, in accordance with the service 

bulletin. After these actions are 

accomplished, no further action is required 

by this paragraph; or 

(2) Blend out corrosion in accordance with 

the service bulletin. 

(i) If blend out of corrosion is beyond 10 

percent of original thickness, or if any crack 

common to the support angles is found 

during accomplishment of the blend out 

procedures, install the new angles with new 

fasteners, and reinstall the threshold 

assembly with new corrosion-resistant 

fasteners, in accordance with the service 

bulletin. After these actions are 

accomplished, no further action is required 

by this paragraph. 

(ii) If blend out of corrosion does not 

exceed 10 percent of original material 

thickness, install the repaired angles with 

new fasteners, and reinstall the threshold 

assembly with new corrosion-resistant 

fasteners, in accordance with the service 

bulletin. After these actions are 

accomplished, no further action is required 

by this paragraph. 

Actions Accomplished According to Previous 

Issue of Service Bulletin 

(s) Installation of a girt bar support fitting 

in accordance with Boeing Service Bulletin 

747–25A2831, dated August 29, 1991, before 

the effective date of this AD, is considered 

acceptable for compliance with the 

corresponding requirements of paragraphs 

(h), (i), (j), (l), (m), and (n) of this AD for each 

affected fitting location. 

New Requirements of This AD 

Inspections for the Washers and Related 

Investigative/Corrective Actions 

(t) For Groups 7, 8, and 9 airplanes 

identified in Boeing Service Bulletin 747–

53A2378, Revision 3, dated August 11, 2005, 

on which the support fitting was replaced or 

repaired in accordance with Boeing Service 

Bulletin 747–53A2378, dated June 24, 1993; 

Revision 1, dated March 10, 1994; or 

Revision 2, dated July 24, 2003; or Boeing 

Service Bulletin 747–25A2831, dated August 

29, 1991: Within 18 months after the effective 

date of this AD, do a general visual 

inspection for correct installation of square 

and conical washers in the girt bar floor 

fittings, and, before further flight, do all 

applicable related investigative and 

corrective actions. Do all actions in 

accordance with Figure 18 and the applicable 

steps specified on page 52 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2378, Revision 3, 

dated August 11, 2005, except as provided by 

paragraph (v) of this AD. 

(u) For Groups 1 through 6 airplanes 

identified in Boeing Service Bulletin 747–

53A2378, Revision 3, dated August 11, 2005, 

on which the support fitting was replaced or 

repaired in accordance with Boeing Service 

Bulletin 747–53A2378, dated June 24, 1993; 

Revision 1, dated March 10, 1994; or 

Revision 2, dated July 24, 2003; or with 

Boeing Service Bulletin 747–25A2831, dated 

August 29, 1991: Within 18 months after the 

effective date of this AD, do a general visual 

inspection to determine if square and conical 

washers are installed in the girt bar floor 

fittings, and before further flight, do all 

applicable related investigative and 

corrective actions. Do all actions in 

accordance with Figure 18 and the applicable 

steps specified on pages 52 and 53 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2378, Revision 3, 

dated August 11, 2005, except as provided by 

paragraph (v) of this AD. 

(v) If any damage is found during any 

inspection required by paragraphs (t) and (u) 

of this AD, and the bulletin specifies 

contacting Boeing for appropriate action: 

Before further flight, do the repair using a 

method approved by the Manager, Seattle 

ACO, FAA, or in accordance with data 

meeting the certification basis of the airplane 

approved by an Authorized Representative 

for the Boeing Commercial Airplanes 

Delegation Option Authorization 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. 

Alternative Methods of Compliance 

(AMOCs) 

(w)(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) AMOCs approved previously in 

accordance with AD 96–23–05, are approved 

as AMOCs for the corresponding provisions 

of this AD. 

Issued in Renton, Washington, on March 7, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–4738 Filed 3–14–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF DEFENSE 

Department of the Army 

32 CFR Part 635 

[Docket No. USA–2007–0007] 

RIN 0702–AA56 

Law Enforcement Reporting 

AGENCY: Department of the Army, DoD. 

ACTION: Proposed rule; request for 

comments. 

SUMMARY: The Department of the Army 

proposes to amend its regulation 

concerning law enforcement reporting. 

The regulation prescribes policies and 

procedures on preparing, reporting, 

using, retaining, and disposing of 

Military Police Reports. The regulation 

prescribes policies and procedures for 

offense reporting and the release of law 

enforcement information. 

DATES: Consideration will be given to all 

comments received by April 16, 2007. 

ADDRESSES: You may submit comments, 

identified by 32 CFR Part 635, Docket 

No. USA–2007–0007 and/or RIN 0702–

AA56, by any of the following methods: 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

• Mail: Federal Docket Management 

System Office, 1160 Defense Pentagon, 

Washington, DC 20301–1160. 

Instructions: All submissions received 

must include the agency name and 

docket number or Regulatory 

Information Number (RIN) for this 

Federal Register document. The general 

policy for comments and other 

submissions from members of the public 

is to make these submissions available 

for public viewing on the Internet at 

http://www.regulations.gov as they are 

received without change, including any 

personal identifiers or contact 

information. 

FOR FURTHER INFORMATION CONTACT: 

James Crumley, (703) 692–6721. 

SUPPLEMENTARY INFORMATION: 

A. Background 

In the December 9, 2005 issue of the 

Federal Register (70 FR 73181) the 

Department of the Army published a 

proposed rule, amending 32 CFR part 


rmajette on PROD1PC67 with PROPOSALS